Multiple-degree of freedom interferometer with compensation for gas effects

ABSTRACT

The disclosure features multiple degree-of-freedom interferometers (e.g., non-dispersive interferometers) for monitoring linear and angular (e.g., pitch and/or yaw) displacements of a measurement object with compensation for variations in the optical properties of a gas in the interferometer measurement (and/or reference) beam paths. The disclosure also features interferometry systems that feature an array of interferometers (e.g., including one or more multiple degree-of-freedom interferometer), each configured to provide different information about variations in the optical properties of the gas in the system. Multiple degree-of-freedom interferometers are also referred to as multi-axis interferometers.

CROSS REFERENCE TO RELATED APPLICATIONS

Under 35 U.S.C. 119(e)(1), this application claims benefit ofProvisional Patent Application No. 60/869,482, entitled “MULTIPLE-DEGREEOF FREEDOM HIGH STABILITY PLANE MIRROR INTERFEROMETER WITH COMPENSATIONFOR TURBULENCE EFFECTS,” filed on Dec. 11, 2006, and to ProvisionalPatent Application No. 60/898,083, entitled “MEASUREMENT ANDCOMPENSATION OF STATIONARY NON-RANDOM EFFECTS OF GAS AND OTHER GASRELATED EFFECTS ON OPTICAL PATH LENGTHS OF MULTI-AXIS INTERFEROMETERS,”filed on Jan. 29, 2007. The entire contents of both Provisional PatentApplication No. 60/869,482 and Provisional Patent Application No.60/898,083 are incorporated herein by reference.

BACKGROUND

Lithography systems are commonly used in fabricating large-scaleintegrated circuits such as computer chips and the like. The function ofa lithography system is to direct spatially patterned radiation onto aphotoresist-coated wafer. The process involves determining whichlocation of the wafer is to receive the radiation (alignment) andapplying the radiation to the photoresist at that location (exposure).

In general, a lithography system, also referred to as a lithographytool, an exposure system or an exposure tool, typically includes anillumination system and a wafer positioning system. The illuminationsystem includes a radiation source for providing radiation such asultraviolet, visible, x-ray, electron, or ion radiation, and a reticleor mask for imparting the pattern to the radiation, thereby generatingthe spatially patterned radiation. In addition, for the case ofreduction lithography, the illumination system can include a lensassembly for imaging the spatially patterned radiation onto the wafer.The imaged radiation exposes resist coated onto the wafer. Theillumination system also includes a mask stage for supporting the maskand a positioning system for adjusting the position of the mask stagerelative to the radiation directed through the mask. The waferpositioning system includes a wafer stage for supporting the wafer andwafer chuck and a positioning system for adjusting the position of thewafer stage relative to the imaged radiation. Fabrication of integratedcircuits can include multiple exposing steps. For a general reference onlithography, see, for example, J. R. Sheats and B. W. Smith, inMicrolithography: Science and Technology (Marcel Dekker, Inc., New York,1998), the contents of which is incorporated herein by reference.

During exposure, the radiation source illuminates the patterned reticle,which scatters the radiation to produce the spatially patternedradiation. The reticle is also referred to as a mask, and these termsare used interchangeably below. In the case of reduction lithography, areduction lens collects the scattered radiation and forms a reducedimage of the reticle pattern. Alternatively, in the case of proximityprinting, the scattered radiation propagates a small distance (typicallyon the order of microns) before contacting the wafer to produce a 1:1image of the reticle pattern. The radiation initiates photo-chemicalprocesses in the resist that convert the radiation pattern into a latentimage within the resist.

Interferometry metrology systems herein after referred to simply asinterferometer systems are typically important components of thepositioning mechanisms that control the positions of the wafer andreticle and register the reticle image on the wafer. Interferometrysystems can be used to precisely measure the positions of each of thewafer stage and mask stage relative to other components of the exposuresystem, such as the lens assembly, radiation source or supportstructure. In such cases, the interferometry system can be attached to astationary structure and a measurement object attached to a movableelement such as one of the mask and wafer stages. Alternatively, thesituation can be reversed, with the interferometry system attached to amovable object and the measurement object attached to a stationaryobject.

More generally, such interferometry systems can be used to measure theposition of any one component of the exposure system relative to anyother component of the exposure system, in which the interferometrysystem is attached to, or supported by, one of the components and themeasurement object is attached, or is supported by the other of thecomponents.

There are various reasons that favor the operation of a lithography toolwith the cavity of the lithography tool filled with a gas instead ofwhere the cavity is evacuated. However, the presence of a dispersivemedium such as the gas in the measurement and reference paths of aninterferometric system used to monitor the position of the stage orstages of the lithography tool introduces uncertainty in measurementsmade using the interferometric system due to the atmospheric effects.

A difficult measurement related to the refractive index of a gas is thecompensation of refractive index fluctuations over a measurement path ofunknown or variable length, with uncontrolled temperature and pressure.An example situation is high-precision distance measuringinterferometry, such as is employed in micro-lithographic fabrication ofintegrated circuits. See for example an article entitled “ResidualErrors In Laser Interferometry From Air Turbulence And Nonlinearity,” byN. Bobroff, Appl. Opt. 26(13), pp 2676-2682 (1987), and an articleentitled “Recent Advances In Displacement Measuring Interferometry,”also by N. Bobroff, Measurement Science & Tech. 4(9), pp 907-926 (1993).As noted in the aforementioned cited references, interferometricdisplacement measurements in a gas are subject to environmentaluncertainties, particularly to changes in air pressure and temperature;to uncertainties in air composition such as resulting from changes inhumidity; and to the effects of turbulence in the gas. Such factorsalter the wavelength of the light used to measure the displacement.Under normal conditions the refractive index of air for example isapproximately 1.0003 with a variation of the order of 1×10⁻⁵ to 1×10⁻⁴.In many applications the refractive index of air must be known with arelative precision of less than 0.1 ppm (parts per million) to less than0.001 ppm, these two relative precisions corresponding to a displacementmeasurement accuracy of 100 nm and less than 1 nm, respectively, for aone meter interferometric displacement measurement.

There are frequent references in the art to heterodyne methods of phaseestimation, in which the phase varies with time in a controlled way. Forexample, in a known form of prior-art heterodyne distance-measuringinterferometer, the source emits two orthogonally polarized beams havingslightly different optical frequencies (e.g. 2 MHz). The interferometricreceiver in this case is typically comprised of a linear polarizer and aphotodetector to measure a time-varying interference signal. The signaloscillates at the beat frequency and the phase of the signal correspondsto the relative phase difference. A further representative example ofthe prior art in heterodyne distance-measuring interferometry is taughtin commonly owned U.S. Pat. No. 4,688,940 issued to G. E. Sommargren andM. Schaham (1987). These known forms of interferometric metrology do notgenerally compensate for fluctuations in refractive index of a gas in ameasurement path of an interferometer.

One way to detect refractive index fluctuations is to measure changes inpressure and temperature along a measurement path and calculate theeffect on the optical path length of the measurement path. Mathematicalequations for effecting this calculation are disclosed in an articleentitled “The Refractivity Of Air,” by F. E. Jones, J. Res. NBS 86(1),pp 27-32 (1981). An implementation of the technique is described in anarticle entitled “High-Accuracy Displacement Interferometry In Air,” byW. T. Estler, Appl. Opt. 24(6), pp 808-815 (1985). This techniqueprovides approximate values, is cumbersome, and corrects for slow,global fluctuations in air density.

Another, more direct way to detect the effects of a fluctuatingrefractive index over a measurement path is by multiple-wavelengthdistance measurement. The basic principle may be understood as follows.Interferometers and laser radar measure the optical path length betweena reference and an object, most often in open air. The optical pathlength is the integrated product of the refractive index and thephysical path traversed by a measurement beam. In that the refractiveindex varies with wavelength, but the physical path is independent ofwavelength, it is generally possible to determine the physical pathlength from the optical path length, particularly the contributions offluctuations in refractive index, provided that the instrument employsat least two wavelengths. The variation of refractive index withwavelength is known in the art as dispersion and this technique is oftenreferred to as the dispersion technique.

An example of a two-wavelength distance measurement system is describedin an article by Y. Zhu, H. Matsumoto, T. O'ishi, SPIE 1319, Optics inComplex Systems, pp 538-539 (1990), entitled “Long-Arm Two-ColorInterferometer For Measuring The Change Of Air Refractive Index.” Thesystem of Zhu et al. employs a 1064 nm wavelength YAG laser and a 632 nmHeNe laser together with quadrature phase detection. Substantially thesame instrument is described in Japanese in an earlier article by Zhu etal. entitled “Measurement Of Atmospheric Phase And Intensity TurbulenceFor Long-Path Distance Interferometer,” Proc. 3rd Meeting On LightwaveSensing Technology, Appl. Phys. Soc. of Japan, 39 (1989). Theinterferometer of Zhu et al. has insufficient resolution forapplications that require sub-micron interferometry such asmicrolithography.

An example of a two-wavelength high-precision interferometry system formicrolithography is represented by U.S. Pat. No. 4,948,254 issued to A.Ishida (1990). A similar device is described by Ishida in an articleentitled “Two Wavelength Displacement-Measuring Interferometer UsingSecond-Harmonic Light To Eliminate Air-Turbulence-Induced Errors,” Jpn.J. Appl. Phys. 28(3), L473-475 (1989). In the article, adisplacement-measuring interferometer is disclosed which eliminateserrors caused by fluctuations in the refractive index by means oftwo-wavelength dispersion detection. An Ar+ laser source provides bothwavelengths simultaneously by means of a frequency-doubling crystalknown in the art as BBO. The use of a BBO doubling crystal results intwo wavelengths that are fundamentally phase locked, thus greatlyimproving the stability and accuracy of the refractive indexmeasurement. However, the motion of the object results in rapidvariations in phase that make it difficult to detect accurately theeffects of fluctuations in the refractive index.

In U.S. Pat. No. 5,404,222 entitled “Interferometric Measuring SystemWith Air Turbulence Compensation,” issued to S. A. Lis (1995), there isdisclosed a two-wavelength interferometer employing the dispersiontechnique for detecting and compensating refractive index fluctuations.A similar device is described by Lis in an article entitled “An AirTurbulence Compensated Interferometer For IC Manufacturing,” SPIE 2440(1995). Improvement on U.S. Pat. No. 5,404,222 by S. A. Lis is disclosedin U.S. Pat. No. 5,537,209. The principal innovation of this system withrespect to that taught by Ishida in Jpn. J. Appl. Phys. (supra) is theaddition of a second BBO doubling crystal to improve the precision ofthe phase detection means. The additional BBO crystal makes it possibleto optically interfere two beams having wavelengths that are exactly afactor of two different. The resultant interference has a phase that isdirectly dependent on the refractive index but is substantiallyindependent of stage motion.

Two two-wavelength distance measuring systems based on superheterodynetechniques are described in commonly owned U.S. Pat. No. 5,764,362entitled “Superheterodyne Method And Apparatus For Measuring TheRefractive Index Of Air Using Multiple-Pass Interferometry” by Henry A.Hill and P. de Groot and U.S. Pat. No. 5,838,485 entitled“Superheterodyne Interferometer And Methods For Compensating TheRefractive Index Of Air Using Electronic Frequency Multiplication” byPeter de Groot and Henry A. Hill. The contents of both of the two citedpatents are herein incorporated in their entirety by reference. In bothof the two referenced patents, contributions to measured phases due toeffects of a gas in a measurement path are directly dependent on therefractive index but the contributions due to stage motion aresubstantially reduced. The first of the two referenced patents is basedon multiple pass interferometry and the second referenced patent isbased on electronic frequency multiplication.

Other commonly owned U.S. Patents relating to dispersion interferometryare U.S. Pat. No. 6,330,065 B1, U.S. Pat. No. 6,327,039 B1, U.S. Pat.No. 6,407,866, U.S. Pat. No. 6,525,825, U.S. Pat. No. 6,525,826 B2, U.S.Pat. No. 6,529,279 and U.S. Pat. No. 6,219,144 B1. The contents of theother commonly owned cited patents are herein incorporated in theirentirety by reference.

A commonly owned U.S. Patent relating to the measurement of intrinsicproperties of a gas such as the reciprocal dispersive power is U.S. Pat.No. 6,124,931 (Γ monitor). The contents of the commonly owned citedpatent are herein incorporated in their entirety by reference.

A non-dispersive apparatus and method for the compensation of turbulenteffects of a gas is described in commonly owned U.S. patent applicationSer. No. 10/350,522 entitled “Method and Apparatus For Compensation OfTime-varying Optical Properties of Gas In Interferometry” by Henry A.Hill. Patent application Ser. No. 10/350,522 compensates for turbulenteffects of the gas on the direction of propagation of a first beam byusing measured effects of the gas turbulence on the directions ofpropagation of the first beam and a second beam. The first and secondbeams are spatially separated and the directions of propagation of thefirst and second beams are substantially parallel. Gas turbulenceeffects on the measurement path length of the first beam are compensatedby using the measured turbulent effects of changes in the direction ofpropagation of the first beam over the measurement path length and aknown relationship between the effects of gas turbulence on thedirection of propagation of a beam and on the corresponding effects onthe optical path length. The contents of cited patent application Ser.No. 10/350,522 are incorporated herein in their entirety by reference.

Another non-dispersive apparatus and method for the compensation ofturbulent effects of a gas is described in commonly owned U.S. patentapplication Ser. No. 10/701,759 entitled “Compensation of RefractivityPerturbations In A Measurement Path Of An Interferometer” by Henry A.Hill. Patent application Ser. No. 10/701,759 compensates for turbulenteffects of the gas on the optical path length of a beam or the averageoptical path length of two beams of an interferometer system by usingmeasured differential effects of the gas turbulence at a singlewavelength on the relative measurement path lengths of a first beam anda second beam wherein cells of the gas that pass through the measurementpath of the first beam are subsequently transported through themeasurement path of the second beam. The directions of propagation ofthe spatially separated first and second beams are substantiallyparallel. The contents of cited U.S. patent application Ser. No.10/701,759 are incorporated herein in their entirety by reference.

Another non-dispersive apparatus and method for the compensation forturbulence effects of a gas is described in commonly owned U.S.Provisional Application No. 60/676,190 entitled “Compensation ofTurbulent Effects Of Gas In Measurement Paths of Multi-AxisInterferometers,” the corresponding utility application Ser. No.11/413,917, and the CIP of U.S. patent application Ser. No. 11/413,917also entitled “Compensation of Turbulent Effects Of Gas In MeasurementPaths of Multi-Axis Interferometers.” The provisional and the twoutility applications are by Henry A. Hill and the contents of the citedprovisional and the two utility applications are incorporated herein intheir entirety by reference.

The effects of stationary changes in the optical path length ofmeasurement paths at a single wavelength are compensated by using aprocedure such as described in commonly owned U.S. Pat. No. 7,075,619 B2entitled “In-Process Correction of Stage Mirror Deformations During aPhotolithography Exposure Cycle” and U.S. Pat. No. 6,842,256 entitled“Compensation For Effects Of Variations In Gas Refractivity InInterferometers.” The two U.S. patents are by Henry A. Hill and thecontents of both thereof are incorporated herein in their entirety byreference.

SUMMARY

The disclosure features multiple degree-of-freedom interferometers(e.g., non-dispersive interferometers) for monitoring linear and angular(e.g., pitch and/or yaw) displacements of a measurement object withcompensation for variations in the optical properties of a gas in theinterferometer measurement (and/or reference) beam paths. The disclosurealso features interferometry systems that feature an array ofinterferometers (e.g., including one or more multiple degree-of-freedominterferometer), each configured to provide different information aboutvariations in the optical properties of the gas in the system. Multipledegree-of-freedom interferometers are also referred to as multi-axisinterferometers.

Variations in the optical properties of gas in interferometer beam in alithography tool can result from a number of different sources. Forexample, turbulence in a gas is one source of such variations. Ingeneral, these sources can be classified as due to stationary or randomeffects. As used herein, “stationary” refers to effects where theprobability-space parameters of a process classified as stationary areinvariant under a translation in time modulo a time interval. In otherwords, the mean and variance of the relevant probability-spaceparameters are related at equivalent stages, e.g., of each exposurecycle of a lithography tool. The aforementioned time interval for agiven lithography tool, for example, can be the reciprocal of the rateat which wafers are processed by the tool. Stationary non-random effectsof a gas and other gas related effects can be further classifiedaccording to whether the effect is generated by an adiabatic ornon-adiabatic process and according to whether the spatial distributionof the effect is nominally isotropic or non-isotropic. Stationarynon-random effects are generally different from turbulence effects inboth temporal and spatial properties. With respect to temporalproperties, turbulence effects are characterized as a non-stationaryeffect in comparison to the temporal properties of stationary non-randomeffects. With respect to spatial properties, stationary effectsgenerally exhibit stationary spatial patterns in addition to stationarytemporal properties. The ordering of the stationary non-random effectsof a gas and other gas related effects can be used in the design of theprocessing of information obtained from the multi-axis interferometersand/or other interferometers in an interferometric system.

An adiabatic change in the optical properties (e.g., refractivity) ofthe gas is the result of changes in gas pressure that occur on timescales set by the speed of sound and the size of an associated cavity.These include acoustic perturbations in a system. A non-adiabaticisotropic change in the optical properties of the gas is the result ofchanges in gas density and/or composition that, e.g., are nominallyspatially isotropic in a plane. The non-adiabatic isotropic changes ingas density and/or composition are classified as nominally isotropicwhen the spatial wavelength of a Fourier component of a change is of theorder of or greater than twice a spatial scale equal to a measurementbeam path length of an interferometer used to detect the respectivechange and classified as non-adiabatic when the Fourier component of thechange is transported as a Lagrangian perturbation, i.e., the Fouriercomponent of the change is transported with the flow of the gas.Non-adiabatic non-isotropic changes in the gas density and/orcomposition are classified as nominally non-isotropic when the spatialwavelength of a Fourier component of a change is less than of the orderof twice a spatial scale equal to a measurement beam path length of aninterferometer used to detect the respective change and classified asnon-adiabatic when the Fourier component of the change is transported asa Lagrangian perturbation.

In certain embodiments, adiabatic effects scale between differentinterferometers in the interferometry system according to lengths of therespective relative measurement path lengths with time delays generallyless than ˜3 msec for cavities with dimensions of the order of 1 m.Non-adiabatic effects can exhibit characteristic time delays betweeninterferometers of the array of interferometers determined by acomponent of the velocity of gas flow and respective spatial separation.For an example of a corresponding component of the velocity of gas flowof 0.5 m/sec and an example of a respective spatial separation of 0.025m, the characteristic time delay is approximately 50 msec. Isotropiceffects scale between different interferometers of the array ofinterferometers according to lengths of the respective relativemeasurement path lengths of the interferometers.

In addition to the contributions of stationary non-random effects of agas and other gas related effects, there can be other contributions tophases measured by interferometers in an interferometry system. Forexample, the other contributions to measured phases in lithography toolscan include oscillations of components of a photolithographic apparatus,stationary effects such as for example body deformation of thephotolithographic apparatus generated by motion of a stage, andnon-stationary effects such as for example body deformation of thephotolithographic apparatus from thermal drift. The effects of the othercontributions are measured and compensated or eliminated in disclosedembodiments.

In some embodiments, an array of interferometers including multi-axisinterferometers is used in conjunction with stored information, e.g.,look up tables, power series or orthogonal representations, aboutstationary effects to obtain information about each of the contributionsclassified as adiabatic, non-adiabatic isotropic, and non-adiabaticnon-isotropic. The interferometers can be configured to yield three ormore independent measurements that have differing sensitivities to eachof the contributions.

In some embodiments, interferometry systems include a multi-axisdisplacement measuring interferometer in conjunction with one or moreinterferometers having a fixed measurement path. Fixed pathinterferometers can be used, for example, to provide additionalcompensation for variations in the optical properties of the gas and/orcompensation for other sources of uncertainty in measurements made usingthe interferometry system. In some embodiments, such as where theinterferometry system is used in a lithography tool, a column referenceinterferometer (CRI) can be used to provide additional compensation.

Alternatively, or additionally, one or more isolated path referenceinterferometers (also referred to as longitudinal referenceinterferometers, or LRI's) can be used to provide additionalcompensation for variations in the optical properties of the gas.Isolated path reference interferometers have a measurement path that isboth fixed in length and thermally isolated from the gas environment inwhich the interferometer is placed. Accordingly, variations in the phasemonitored using an LRI are, in general, due to adiabatic changes in thesystem or changes in the wavelength of the input beam.

In some embodiments, non-dispersive apparatus are used to compensate,e.g., by a factor about 10 or more, for effects of turbulence on theoptical properties of the gas that exhibit temporal frequencies of theorder of the inverse of a spacing between different measurement beampaths of a multi-axis interferometer times the characteristic speed ofgas flow across the paths of the multi-axis interferometer.

Embodiments include processing of a first difference parameter (FDP)wherein neither accurate knowledge of the orientation or position of arespective measurement and/or reference object mirrors of theinterferometer is required. In certain embodiments, measurement of FDPis made with a plane mirror interferometer configured withmultiple-measurement beam paths such that FDP is based on multiplesingle pass linear displacement measurements of the measurement objectmirror. The FDP can be invariant to displacements of the measurementobject mirror in the direction orthogonal to the respective mirrorsurface that may occur prior to and/or during the acquisition of thelinear displacement measurements and are invariant up through firstorder effects with respect to changes in orientation of the mirrors.Other second and higher order difference parameters may also bebeneficially used.

FDP can be related to first and higher order temporal and/or spatialderivatives of effects on measured optical paths of gas turbulence andacoustic perturbations of gas properties. The first and higher ordertemporal or spatial derivatives of the effects are inverted either bycombinations of Fourier transforms and associated inverse Fouriertransforms, by direct integrations with respect to the correspondingtemporal or spatial coordinates, or by use of Fourier series techniquesto generate a contemporaneous measurement of gas turbulence effects andacoustic perturbation effects on measurements of linear and angulardisplacements of objects by the interferometer. The contemporaneouslymeasured values are used for compensating the gas turbulence effects andacoustic perturbation effects of gas properties on the measurements oflinear and angular displacements of objects.

In some embodiments, measurements of gas turbulence and acoustic effectson the optical path lengths of reference and measurement beams areachieved by conditioning an input beam prior to directing the input beamto reference and measurement objects of the interferometer. Beam shearcan also be reduced (e.g., eliminated) in an interferometric system bythe conditioning of the input beam. Accordingly, in certain aspects, thedisclosure features apparatus and methods for enabling measurements ofgas turbulence and acoustic effects and reducing beam shear in aninterferometer and/or for reducing beam shear of measurement beams atthe reference and measurement objects of an interferometer. Conditioningthe input beam can reduce beam shear associated with changes in theposition (e.g., orientation and/or displacement relative to a referenceframe) of a measurement object (e.g. plane mirror or retroreflector).Conditioning the input beam refers to adjusting the relative directionof propagation and/or location of the beam relative to a referencesystem to compensate for changes in the beam's path in theinterferometer that are introduced by changes in the measurement objectorientation. Conditioning of the input beam can be achieved passively.

Embodiments can include a section that conditions properties of an inputbeam to form a conditioned input beam, which is then directed to aninterferometer. The interferometer splits the conditioned input beaminto a measurement beam and a reference beam. The beam conditioningsection can include components that compensate for changes in thepropagation of the measurement beam that would be caused by changes inthe orientation of the measurement object. The beam conditioning sectioncan also include components that compensate for beam shear that may beintroduced during the beam conditioning to minimize shear of theconditioned input beam at the interferometer and/or at the measurementobject.

Other beams can be derived from the conditioned input beam prior to theinterferometer. For example, a portion of the conditioned input beam canbe directed to a first detector for determining a change in anorientation of the measurement object. Alternatively, or additionally, aportion of the conditioned input beam can be directed to an angleinterferometer such as described in subsequently referenced U.S. Pat.No. 6,563,593 B2, U.S. Pat. No. 6,552,804 B2, and U.S. Pat. No.6,917,432. Angle interferometers can be used to monitor changes in thedirection of propagation of the conditioned input beam relative to anoptical axis defined by the beam conditioning portion.

For embodiments where the measurement object is a plane mirror,conditioning the input beam can cause the measurement beam to have adirection of propagation that is substantially orthogonal to thereflecting surface of the plane mirror for a range of orientationangles. As the orientation of the measurement object varies within thisrange of angles, beam conditioning ensures that the measurement beamretains normal incidence at the measurement object. Accordingly, shearbetween the reference and measurement components both within theinterferometer, in the output beam, and at the measurement object thatcould result from such changes in measurement object orientation isreduced. Effects of gas turbulence and acoustic perturbations can bereduced in the conditioned input beam (e.g., eliminated). Alternatively,or additionally, effects on properties of the conditioned input beamfrom departures of the surface of the measurement object from areference plane mirror surface can be reduced (e.g., eliminated upthrough first order spatial derivatives).

In addition, the reference and measurement beam components of theconditioned input beam can have substantially zero shears at the inputof one or more interferometers used to measure changes in the positionof the measurement object.

In embodiments, the measurement object is used as an integral part ofthe apparatus in conditioning the input beam to form the conditionedinput beam. The input beam is typically directed to contact themeasurement object at least once in the conditioning portion of theapparatus. In heterodyne interferometry, both frequency components ofthe input beam are directed to contact measurement object. Accordingly,any change in the position of the measurement object from a referenceposition causes a change in the propagation direction/beam locationrelative to a path defined by the reference position.

In some embodiments, interferometers are used in conjunction with aplanar encoder apparatus for measuring and compensating stationarynon-random effects of a gas and other gas related effects on accuracy ofinterferometric measurements. Stationary non-random effects not relatedto the gas and vibrations that affect the measurement and compensationfor the stationary non-random effects of the gas and the other gasrelated effects can also be measured and compensated.

The interferometric and planar encoder apparatus and method used indisclosed embodiments comprise apparatus and methods for thecompensation of stationary non-random effects of a gas and other relatedeffects of the gas on accuracy of interferometric measurements of achange in linear and angular displacement of an object. The apparatusand methods may also comprise measurement of intrinsic properties of thegas such as the reciprocal power of the gas.

In certain embodiments, the interferometric apparatus generatesmeasurement of first and/or higher order spatial or temporal derivativesof effects of gas turbulence and acoustic perturbations on measuredoptical paths in interferometers. The first and/or higher order spatialor temporal derivatives of the effects can be integrated with respect tothe corresponding spatial coordinate or inverted by a combination ofFourier transforms and inverse Fourier transforms to generate acontemporaneous measurement of gas turbulence and acoustic perturbationeffects on measurements of linear and angular displacements by theinterferometers. The contemporaneously measured values are used forcompensating the gas turbulence and acoustic perturbation effects on themeasurements of linear or angular displacements.

The effects of stationary non-random changes in the optical path lengthof measurement paths at the single wavelength of a non-dispersiveinterferometer can be compensated by using a procedure such as describedin commonly owned U.S. patent application Ser. No. 10/294,158 entitled“COMPENSATION FOR EFFECTS OF VARIATIONS IN GAS REFRACTIVITY ININTERFEROMETERS” by Henry A. Hill. The contents of the patentapplication are incorporated herein in their entirety by reference. Theeffects of stationary changes are compensated by using a procedure suchas described in U.S. Provisional Patent Application No. 60/644,898entitled “MULTI-AXIS INTERFEROMETER AND DATA PROCESSING FOR MIRRORMAPPING.” Provisional Patent Application No. 60/644,898 is by Henry A.Hill and Gary Womack and the contents thereof are incorporated herein intheir entirety by reference.

Planar encoder metrology systems are generally used herein in disclosedembodiments in the identification in situ of the effects of stationarynon-random effects present in interferometric metrology systems.

In general, in a first aspect, the invention features a method,including conditioning a first input beam and a second input beam,forming a conditioned output beam from the conditioned first input beamand the conditioned second input beam, the conditioned output beamcomprising a first interferometric phase including information about anoptical path difference between the conditioned first input beam and theconditioned second input beam, deriving a first measurement beam and afirst reference beam from the conditioned first input beam andconditioned second input beam, respectively, using an optical assemblyand directing the first measurement beam to reflect from a measurementobject remote from the optical assembly, wherein the conditioning causesthe first measurement beam to be normally incident on the measurementobject for a range of orientation angles of the measurement object withrespect to the optical assembly, combining the first measurement beamand the first reference beam to form a first output beam including asecond interferometric phase including information about an optical pathdifference between the first reference and measurement beams, detectingthe conditioned output beam and the first output beam and monitoring thefirst and second interferometric phases based on the detectedconditioned output beam and first output beam, respectively, monitoringa degree of freedom of the measurement object based the secondinterferometric phase, and reducing uncertainty in the monitored degreeof freedom due to variations in the optical properties of a gas betweenthe optical assembly and the measurement object based on the informationfrom the first and second interferometric phases.

Implementations of the method can include one or more of the followingfeatures and/or features of other aspects. For example, conditioning thefirst input beam can include directing the first input beam to reflectfrom the measurement object. The first input beam can be directed toreflect from the measurement object twice. Conditioning the first inputbeam can cause the conditioned first input beam to be perpendicular tothe measurement object for a range of orientation angles of themeasurement object with respect to the optical assembly when it reflectsfrom the measurement object the second time. Conditioning the firstinput beam can include directing the first input beam through anelliptical aperture.

In some embodiments, conditioning the second input beam includesdirecting the second input beam to reflect from the measurement object.The first input beam and the second input beam can be directed toreflect from the measurement object along parallel paths. The secondinput beam can be directed to reflect from the measurement object twice.The first input beam path on its first pass to the measurement objectcan be co-planar with the second input beam path on its second pass tothe measurement object. The first input beam path on its second pass tothe measurement object can be co-planar with the second input beam pathon its first pass to the measurement object.

The first and second interferometric phases can include informationabout imperfections in a surface of the measurement object and reducinguncertainty comprises reducing uncertainty due to the imperfectionsbased on the information from the first and second interferometricphases.

The first input beam and the second input beam can be derived from acommon source.

The method can include flowing gas between the measurement object andthe optical assembly. The gas can be flowed in a direction substantiallyperpendicular to the measurement beam path. The first and second inputbeams can be directed along corresponding paths to reflect a first timefrom the measurement object and the gas is flowed parallel to a planedefined the paths.

The first interferometric phase can include a term that is proportionalto a spatial derivative of a term characterizing optical properties ofthe gas in the path of the first input beam between the optical assemblyand the measurement object.

In certain embodiments, the method further includes deriving a secondmeasurement beam and a second reference beam from the conditioned secondinput beam and conditioned first input beam, respectively, using theoptical assembly and directing the second measurement beam to reflectfrom the measurement object, combining the second measurement beam andthe second reference beam to form a second output beam including a thirdinterferometric phase including information about an optical pathdifference between the second reference and second measurement beams,and detecting the second output beam and monitoring the thirdinterferometric phase based on the detected second output beam, whereinthe first and second input beams are derived from a common source.Reducing uncertainty in the monitored degree of freedom can includedetermining values of a first difference parameter from the second andthird interferometric phases. The method can include determininginformation about a surface figure of the measurement object based onthe values of the first difference parameter. Reducing uncertainty inthe monitored degree of freedom can include inverting the values of thefirst difference parameter to obtain information about contributions ofvariations in the optical properties of the gas to the monitoredinterferometric phases of the first and second output beams. Invertingthe values can include using a Fourier series or Fourier transformtechnique. A spacing between locations on the measurement object betweenthe first and second measurement beams can be selected so that a regionof low sensitivity of the Fourier series or Fourier transform techniquecorresponds to a frequency region where contributions of acousticperturbations and turbulence to the monitored second and thirdinterferometric phases is minimal.

In another aspect, the invention features a lithography method for usein fabricating integrated circuits on a wafer, the method includingsupporting the wafer on a movable stage, imaging spatially patternedradiation onto the wafer, adjusting the position of the stage, andmonitoring the position of the stage using the above-mentioned method,wherein the measurement object is attached to the stage and the positionof the stage is monitored from the monitored degree of freedom of themeasurement object with reduced uncertainty.

In a further aspect, the invention features a lithography method forfabricating integrated circuits on a wafer including positioning a firstcomponent of a lithography system relative to a second component of alithography system to expose the wafer to spatially patterned radiation,and monitoring the position of the first component relative to thesecond component using the above-mentioned method, wherein themeasurement object is attached to the first component and the positionof the first component is monitored from the monitored degree of freedomof the measurement object with reduced uncertainty.

In general, in a further aspect, the invention features a method,including directing a first input beam and a second input beam toreflect from a measurement object, forming a first output beam from thefirst input beam after it reflects from the measurement object bycombining the first input beam with the second beam, the first outputbeam including a first interferometric phase including information aboutan optical path difference between the first and second input beams,deriving a first measurement beam from the first input beam and derivinga first reference beam from the second input beam using an opticalassembly and directing the first measurement beam to reflect from themeasurement object, combining the first measurement beam and the firstreference beam to form a second output beam including a secondinterferometric phase including information about an optical pathdifference between the first reference and measurement beams, detectingthe first and second output beams and monitoring the first and secondinterferometric phases based on the detected output beams, monitoring adegree of freedom of the measurement object based the secondinterferometric phase, and reducing uncertainty in the monitored degreeof freedom due to variations in the optical properties of a gas betweenthe optical assembly and the measurement object based on the informationfrom the first and second interferometric phases.

Implementations of the method can include one or more of the featuresdiscussed in relation to other aspects.

In general, in another aspect, the invention features a system,including a light source configured to produce a primary beam, a beamconditioning assembly configured to receive the primary beam, to derivea first input beam and a second input beam from the primary beam, todirect the first and second input beams to reflect from a measurementobject at least once, and to output a first conditioned input beam and asecond conditioned input beam, an interferometer assembly remote fromthe measurement object, the interferometer assembly being configured toreceive the first and second conditioned input beams, to derive a firstmeasurement beam from the first conditioned input beam and a firstreference beam from the second conditioned input beam, to direct thefirst measurement and reference beams along different paths where thefirst measurement beam reflects from the measurement object, theinterferometer assembly being further configured to combine the firstmeasurement and reference beams to produce a first output beam includinga first interferometric phase including information about a degree offreedom of the measurement object, a first detector configured to detectthe first output beam, and an electronic processor in communication withthe first detector, the electronic processor being configured todetermine information about the degree of freedom of the measurementobject based on the interference phase of at least one of the outputbeams and to reduce uncertainty in the degree of freedom due tovariations in the optical properties of a gas between the interferometerassembly and the measurement object based on the first interferometricphase.

Embodiments of the system can include one or more of the followingfeatures and/or features of other aspects. For example, the beamconditioning assembly can be configured to direct the first and secondinput beams to reflect from the measurement object twice. For a range oforientation angles of the measurement object with respect to theinterferometry assembly, the first and second input beams can benormally incident on the measurement object upon the second reflectionfrom the measurement object.

The interferometer assembly can be configured to derive a secondmeasurement beam from the second conditioned input beam and a secondreference beam from the first conditioned input beam, to direct thesecond measurement and reference beams along different paths where thesecond measurement beam reflects from the measurement object, theinterferometer assembly being further configured to combine the secondmeasurement and reference beams to produce a second output beamincluding an interferometric phase including information about a seconddegree of freedom of the measurement object. The system can include asecond detector configured to detect the second output beam, the seconddetector being in communication with the electronic processor. The pathsof the first and second measurement beams can be parallel between theinterferometer assembly and the measurement object. The beamconditioning assembly can be further configured to derive a conditionedoutput beam from each of the first and second conditioned input beamsand to combine the two conditioned output beams to provide a combinedconditioned output beam, the combined conditioned output beam includingan interferometric phase including information about an optical pathdifference between the first conditioned input beam and the secondconditioned input beam. The conditioned output beam can include a secondinterferometric phase including information about variations in theoptical properties of a gas in the paths of the two conditioned inputbeams. The system can include a detector configured to detect theconditioned output beam, the detector being in communication with theelectronic processor, wherein the electronic processor is configured toreduce uncertainty in the degree of freedom due to variations in theoptical properties of a gas between the interferometer assembly and themeasurement object based on the second interferometric phase.

The interferometry assembly can direct the first measurement beam toreflect from the measurement object only once. The beam conditioningassembly can be configured so that for a range of orientation angles ofthe measurement object with respect to the interferometry assembly, thefirst measurement beam is normally incident on the measurement objectfor the second reflection.

The measurement object can be a plane mirror measurement object. Themeasurement object can be attached to a wafer stage of a lithographytool. The interferometry assembly and beam conditioning assembly can beattached to frame of the lithography tool.

In another aspect, the invention features a lithography system for usein fabricating integrated circuits on a wafer, the system including anillumination system for imaging spatially patterned radiation onto thewafer, the above-mentioned system configured to monitor a position ofthe wafer relative to the imaged radiation, wherein wafer is supportedby a movable stage and the measurement object is attached to the stage;and a positioning system for adjusting the position of the stagerelative to the imaged radiation. The lithography system can be a dualstage lithography system.

In another aspect, the invention features a lithography system for usein fabricating integrated circuits on a wafer, the system including anillumination system including a radiation source, a mask, a positioningsystem, a lens assembly, and the above-mentioned system, wherein duringoperation the source directs radiation through the mask to producespatially patterned radiation, the positioning system adjusts theposition of the mask relative to the radiation from the source, the lensassembly images the spatially patterned radiation onto the wafersupported by the stage, and the system monitors the position of the maskrelative to the radiation from the source.

In general, in another aspect, the invention features a system,including a movable stage configured to support a wafer and position thewafer relative to a projection lens, a first interferometer configuredto direct a first measurement beam along a path between a firstmeasurement object attached to the projection lens and a firstinterferometer assembly located remote from the projection lens, thefirst interferometer being configured to form a first output beam fromthe first measurement beam, the first output beam including a firstinterferometric phase including information about variations in anoptical path length of the path between the first measurement object andthe first interferometry assembly, a first detector configured to detectthe first output beam, a second interferometer configured to direct asecond measurement beam along a path between a second measurement objectattached to the stage and a second interferometer assembly locatedremote from the stage, the second interferometer being configured toform a second output beam from the second measurement beam, the secondoutput beam including a second interferometric phase includinginformation about variations in an optical path length of the pathbetween the second measurement object and the second interferometryassembly, a second detector configured to detect the second output beam,an electronic processor in communication with the first and seconddetectors, the electronic processor being configured to monitor a degreeof freedom of the stage based on the second interferometric phase and toreduce uncertainty in the monitored degree of freedom due to variationsin the optical properties in a gas in the path of the second measurementbeam based on the first and second interferometric phases.

Embodiments of the system can include one or more of the followingfeatures and/or features of other aspects. For example, the first andsecond measurement beam paths can be in a path of a gas flow of gasintroduced into an enclosure housing the stage. The first and secondmeasurement beam paths can be parallel. The first measurement beam pathcan be sufficiently far from the stage so that gas turbulence due tomovement of the stage does not cause substantial variations in theoptical properties of the gas in the first measurement path.

The first interferometer can be a column reference interferometer. Thesecond interferometer can be a multi-axis interferometer. The secondinterferometer can include a single pass interferometer. The secondinterferometer can include a plurality of single pass interferometers.The second interferometer can include a beam conditioning assembly.

The measurement object can be a plane mirror measurement object.

The system can include a third interferometer positioned remote from thestage, the third interferometer being a fixed measurement beam pathinterferometer where the measurement beam path is isolated from the gasin the second measurement beam path. The third interferometer can bepositioned close to the second interferometer (e.g., sufficiently closeso that adiabatic changes in the path of the measurement beam of thethird interferometer are similar to the adiabatic changes in the path ofthe measurement beam of the second interferometer). The system canfurther include a third detector configured to detect a third outputbeam from the third interferometer, the third detector being incommunication with the electronic processor and the electronic processorbeing configured to reduce uncertainty in the monitored degree offreedom due to variations in the optical properties of the gas based onthe information in the third output beam. In some embodiments, thesystem includes a plurality of interferometers including the thirdinterferometer, the plurality of interferometers being positioned atlocations remote from the stage, each of the plurality interferometersbeing fixed measurement beam path interferometers where the measurementbeam path of each is isolated from the gas in the second measurementbeam path. The third interferometer can be a wavelength meter.

In certain embodiments, the system includes an optical encoderconfigured to monitor a degree of freedom of the stage.

In another aspect, the invention features a lithography system for usein fabricating integrated circuits on a wafer, the system including aprojection lens for imaging spatially patterned radiation onto thewafer, the above-mentioned system for monitoring the position of thewafer relative to the imaged radiation, and a positioning system foradjusting the position of the stage relative to the imaged radiation,wherein the wafer is supported by the stage. The lithography system canbe a dual stage lithography system.

In a further aspect, the invention features a lithography system for usein fabricating integrated circuits on a wafer, the system including anillumination system including a radiation source, a mask, a positioningsystem, a projection lens, and the above-mentioned system, whereinduring operation the source directs radiation through the mask toproduce spatially patterned radiation, the positioning system adjuststhe position of the mask relative to the radiation from the source, theprojection lens images the spatially patterned radiation onto the wafersupported by the stage, and the system monitors the position of the maskrelative to the radiation from the source. The lithography system can bea dual stage lithography system. The lithography system can be animmersion lithography system.

In general, in a further aspect, the invention features an electronicsmodule, including a first terminal configured to receive a signal from acolumn reference interferometer in a photolithography tool, a secondterminal configured to receive a signal from a second interferometerconfigured to monitor a degree of freedom of a stage in thephotolithography tool, and an electronics processor configured tomonitor a degree of freedom of the stage based on the signal from thesecond interferometer and to reduce uncertainty in the monitored degreeof freedom due to variations in the optical properties in a gas in apath of a measurement beam of the second interferometer based on thesignals from the column reference interferometer and the secondinterferometer.

Embodiments may have one or more of the following advantages.

The systems and methods disclosed herein can provide accuratemeasurements of stage position and/or orientation in a lithography tool(e.g., a single or dual stage lithography tool). For example, themeasurements can account for variations in the optical properties of agas in a measurement beam path between the stage and interferometer aswell as other sources of error, such as vibrations in the tool. As aresult, measurements made using such interferometric metrology systemsin a lithography tool can be compensated down to the sub-nanometerlevel.

The signal used in embodiments to compensate for variations in theoptical properties of a gas (e.g., gas turbulence and acousticperturbation effects) can be generated with zero data age.

Effects of first and higher order spatial derivatives of departures ofthe surface of the measurement object from a reference plane mirrorsurface can be measured in situ.

The “common mode” beam shear in the passive zero-shear interferometersat the input of the one or more interferometers can be approximately oneto two orders of magnitude smaller than that present in a standard highstability plane mirror interferometer (HSPMI). The maximum common modebeam shear in the passive zero-shear interferometers can be 20 to 100microns.

There can be reduced “differential mode” beam shear between thereference and measurement beams at a distance or angle measuringinterferometer of a passive zero-shear interferometer. For example,there can be no differential mode beam shear between reference andmeasurement beams at a distance or angle measuring interferometer of apassive zero-shear interferometer for a range of positions of themeasurement object relative the interferometer. The maximum differentialmode beam shear in the input of the one or more interferometers can beless than or of the order of 5 microns.

There can be reduced differential mode beam shear (e.g., substantiallyno differential mode beam shear) between the reference and measurementbeams at the detector of a passive zero-shear interferometer. Themaximum differential mode beam shear at the detector can be less than orof the order of 5 microns. This feature can simplify fiber-optic pickup(FOP) vis-à-vis non-linear non-cyclic errors for use of both single modeand multi-mode fiber optics. This feature can also reduce (e.g.,eliminate), by two or more orders of magnitude, the non-linearnon-cyclic errors caused by beam shear and wavefront errors that areintroduced by elements of the interferometer excluding the measurementobject. The non-linear non-cyclic error caused a wavefront errorintroduced by the measurement object can be reduced by a factor of fouror more depending upon the spatial properties of the wavefront error.Reduction of the differential mode beam shear in the passive zero-shearinterferometer can permit use of smaller diameter beams in the presenceof relatively large changes in orientation of the measurement objectmirror. The reduction of the differential mode beam shear in the passivezero-shear interferometer can relax optical tolerances on interferometerand detector elements required to achieve a specified level of systemperformance.

The measurement beam in a passive zero-shear interferometer of thepresent invention can be always normal to the reflecting surface of ameasurement object mirror, for at least a range of orientation angles ofthe measurement object mirror.

There can be no moving parts, i.e., no dynamic elements, in a passivezero-shear interferometer of the present invention.

The passive zero-shear interferometers can be configured to operate assingle pass plane mirror interferometers. The corresponding passivezero-shear single pass plane mirror interferometer can have a reducednumber of sources of cyclic error the same as with the dynamicinterferometer such as described in commonly owned U.S. Pat. No.6,563,593 B2 entitled “DYNAMIC ANGLE MEASURING INTERFEROMETER,” U.S.Pat. No. 6,552,804 B2 entitled “APPARATUS AND METHOD FOR INTERFEROMETRICMEASUREMENTS OF ANGULAR ORIENTATION AND DISTANCE TO A PLANE MIRROROBJECT,” and U.S. Pat. No. 6,917,432 entitled “INTERFEROMETERS FORMEASURING CHANGES IN OPTICAL BEAM DIRECTION” all by Henry A. Hill. Thecontents of the three cited U.S. Patents are herein incorporated intheir entirety by reference. Alternatively, the passive zero-shearinterferometer can be configured to operate as a double pass planemirror interferometer or as a multi-pass plane mirror interferometerwhere the number of passes is three or more.

Sub-harmonic cyclic errors present in multiple pass interferometers ofthe pitch-yaw-displacement section of a passive zero-shearinterferometer can be eliminated as a result of separated beam paths.

The beam shear at the measurement object mirror in a passive zero-shearinterferometer can be ¼ of the beam shear generated by the second passbeam to the measurement object mirror in a double pass plane mirrorinterferometer, e.g., a HSPMI.

The measurement object (e.g., measurement object mirror) can be smallerwhen using a passive zero-shear interferometer. Similarly, theinterferometer components in the passive zero-shear interferometer canbe smaller relative to comparable systems.

The interference signal amplitude in a passive zero-shear interferometerof the present invention can be independent of pitch and yaw. Thisfeature can improve efficiency of the interferometer system with respectto laser beam intensity by a factor of about 2 to 3. The factor may beeven larger when considering properties of a standard HSPMI in thecontext of a large maximum beam shear such as 4 mm.

A passive zero-shear single pass plane mirror interferometer can be usedwith passive angle interferometers, i.e., angle detectors that have nomoving parts. Examples of passive angle interferometers are thosedeveloped for the dynamic interferometer to measure pitch, yaw, anddisplacement based on a single measurement beam contacting themeasurement object mirror (see referenced U.S. Pat. No. 6,563,593 B2,U.S. Pat. No. 6,552,804 B2, and U.S. Pat. No. 6,917,432).

Certain of the surface properties of measurement object mirrors can becharacterized in-situ in a litho-tool configured with a metrology systembased on passive zero-shear single pass plane mirror interferometers andno additional reference flats are required.

The passive zero-shear interferometer can be placed on a moving stagewith the measurement object mirrors located off the stage.

In some embodiments, a passive zero-shear interferometer can be alignedat the factory with no additional alignment of the passive zero-shearinterferometer required in the field.

The passive zero-shear feature of the passive zero-shear interferometerscited with respect to a zero relative shear of output reference andmeasurement beams can also mean that portions of the input reference andmeasurement beams conjugate to the reference and measurement outputbeams, respectively, exhibit no lateral shear (this is not necessarilythe case for example with a HSPMI used with a measurement object mirrorthat experiences changes in orientation).

Another advantage of disclosed embodiments is that a metrology systemincluding an interferometer metrology system and a planar encodermetrology system reduces the requirements placed on the encoder system,e.g., the encoder system does not have to handle a set of redundancyproblems or the spatial patterns on the encoder scales may be a simpletwo dimensional grating.

Another advantage is that a planar encoder metrology system of ametrology system including an interferometer metrology system and theencoder metrology system does not have to include absolute planarencoders.

Another advantage is that the measurement of stationary non-randomeffects of gas in a metrology system including an interferometermetrology system and a planar encoder metrology system is performed insitu.

Another advantage of disclosed embodiments is a compensation for effectsof mechanical resonances and vibrations that are detected with differentefficiencies in, for example, column reference interferometers in alithography tool, interferometer metrology systems that measure andmonitor the position of a stage of the lithography tool, and aninterferometer used to measure and monitor adiabatic changes in the gasof the lithography tool.

Another advantage is a compensation for adiabatic effects wherein datarelating to measurement and monitoring of the adiabatic effects is notsegmented or fragmented by the exchange of stages or wafer chucks indual stage lithography tools, i.e., a reduced initialization problem.

Another advantage is a compensation for non-adiabatic isotropic effects,e.g., such as measured by a column reference interferometer, whereindata relating to measurement and monitoring of the non-adiabaticisotropic effects is not segmented or fragmented with the exchange ofstages or wafer chucks in dual stage lithography tools, i.e., a reducedinitialization problem.

Another advantage is a compensation for non-adiabatic isotropic effectswherein the non-adiabatic isotropic effects, e.g., such as measured by acolumn reference interferometer, are scalable to match optical pathlengths of other interferometers of an interferometer metrology system.

Another advantage is a compensation for non-adiabatic non-isotropiceffects wherein data relating to measurement and monitoring of thenon-adiabatic non-isotropic effects may be segmented or fragmented withthe exchange of stages or wafer chucks in dual stage lithography toolsby the exchange of stages or wafer chucks or may not be segmented orfragmented in a single stage lithography tool.

Another advantage is a compensation for effects of gas compositionchanges due to exposure of a wafer in a non-immersion or an immersionlithography tool wherein the effects of composition changes are treatedas stationary non-random effects.

Another advantage is a compensation for low order gradients innon-adiabatic effects in interferometer metrology systems with the useof two or more interferometers (e.g., LRI's) that measure and monitoradiabatic changes in the gas of a lithography tool.

Another advantage is an initialization for stationary effects ininterferometer metrology systems wherein data relating to measurementand monitoring of the non-adiabatic non-isotropic effects are segmentedor fragmented by the exchange of stages or wafer chucks in dual stagelithography tools.

Another advantage is that sections of planar encoders used in planarencoder metrology systems for measurement and monitoring of stationaryeffects may be located on a wafer chuck.

Another advantage is that sections of planar encoders used in planarencoder metrology systems for measurement and monitoring of stationaryeffects may be located in the kerfs of in process wafers.

Another advantage is that stationary effects in column referenceinterferometers, e.g., such as generated by body deformation from stagemotion and body deformation from thermal drift, are measured andmonitored.

Another advantage is that stationary non-random effects of gas can beincorporated in the initialization of an interferometer metrology systemassociated with the exchange of a stage or wafer chuck.

The details of one or more embodiments are set forth in the accompanyingdrawings and the description below. Other features and advantages willbe apparent from the description and drawings.

BRIEF DESCRIPTION OF DRAWINGS

The structure and operation of embodiments disclosed herein may best beunderstood by reading the detailed description in conjunction with thedrawings wherein disclosed embodiments' parts have assigned referencenumerals that are used to identify them in all of the drawings in whichthey appear and wherein:

FIG. 1 is a schematic perspective view of an interferometer system thatmonitors the position of an object and compensates for effects of theoptical properties of a gas in the measurement and/or reference paths ofthe interferometer system.

FIG. 2 a is an exploded perspective view of an interferometer systemthat compensates for turbulence and acoustic perturbation effects of gasin a measurement or reference beam path.

FIG. 2 b is a diagram of the measurement beam spots on a measurementobject of the interferometer system shown in FIG. 2 a.

FIG. 3 a is an exploded perspective view of another section of amulti-axis plane mirror interferometer system including the firstsection of the multi-axis interferometer system shown in FIG. 2 a thatmeasures and monitors the effects of other related effects of gas, e.g.,turbulence and acoustic effects, in a lithography tool.

FIG. 3 b is a diagram of the measurement/reference beam spots on ameasurement object of the interferometer system shown in FIGS. 2 a and 3a.

FIG. 4 is a schematic perspective view of another interferometer systemthat monitors the position of an object and compensates for effects ofthe optical properties of a gas in the measurement and/or referencepaths of the interferometer system.

FIG. 5 is a schematic perspective view of an interferometer system andencoders system that monitors the position of an object and compensatesfor effects of the optical properties of a gas in the measurement and/orreference paths of the interferometer system.

FIG. 6 is a flowchart showing steps in example of an algorithm forimplementing error correction for interferometric stage mirrormeasurements

FIG. 7 is a schematic diagram of a lithography tool.

FIG. 8 a and FIG. 8 b are flow charts that describe steps for makingintegrated circuits.

FIG. 9 is a schematic of a beam writing system that includes aninterferometry system.

Like reference symbols in the various drawings indicate like elements.

DETAILED DESCRIPTION

Reference is made to FIG. 1 which is a diagrammatic perspective view ofan interferometric system 15 that employs a pair of orthogonallyarranged interferometers or interferometer subsystems by which thelocation and orientation of on-stage mounted stage mirrors may bemeasured in situ with high spatial resolution along one or more datumlines and by which effects of a dispersive medium such as a gas in themeasurement and/or reference beam paths may be compensated. As shown inFIG. 1, system 15 comprises a stage 16 that forms part of aphotolithographic apparatus for fabricating semiconductor products suchas integrated circuits or chips. Affixed to stage 16 is a plane stagemirror 50 having a y-z reflective surface 51 elongated in they-direction.

Also, fixedly mounted to stage 16 is another plane stage mirror 60having an x-z reflective surface 61 elongated in the x-direction.Mirrors 50 and 60 are mounted on stage 16 so that their reflectivesurfaces, 51 and 61, respectively, are nominally orthogonal to oneanother. Stage 16 is otherwise mounted for nominally plane translationbut may experience small angular rotations about the x, y, and z axesdue to bearing and drive mechanism tolerances. In normal operation,system 15 is adapted to be operated for scanning in the y-direction forset values of x.

Fixedly mounted off-stage is an interferometer (or interferometersubsystem) that is generally indicated at 10. The purpose ofinterferometer 10 generally is to measure using non-dispersiveinterferometry a FDP of reflecting surface 51 and of the gas in themeasurement beam paths of interferometer 10 and to measure the positionof stage 16 in the x-direction and the angular rotations of stage 16about the y- and z-axes as stage 16 translates in the x- andy-direction. Interferometer 10 comprises plane interferometers such asinterferometer 100 shown in FIG. 2 a and arranged so thatinterferometric beams travel to and from mirror 50 generally along anoptical path designated as 12.

Also fixedly mounted off-stage is an interferometer (or interferometersubsystem) that is generally indicated at 20. The purpose ofinterferometer 20 generally is to measure using non-dispersiveinterferometry a FDP of reflecting surface 61 and of the gas in themeasurement beam paths of interferometer 20, the position of stage 16 inthe y-direction, and the angular rotations of stage 16 about the x- andz-axes as stage 16 translates in the x- and y-direction in addition toother information such as used in mapping surface 61 of mirror 60.Interferometer 20 comprises plane interferometers such as interferometer100 shown in FIG. 2 a and arranged so that interferometric beams travelto and from mirror 60 generally along an optical path designated as 22.

The signals from interferometers 10 and 20 are processed by electronicprocessor 17.

In embodiments of the present invention, interferometer subsystems 10and 20 may comprise apparatus and methods of non-dispersiveinterferometry in combination for the compensation of effects of adispersive medium such as a gas in the measurement and/or reference beampaths of the respective interferometer subsystems 10 and 20.Interferometer subsystems 10 and 20 may comprise arefractometer/wavelength monitor or monitors.

Embodiments relate to apparatus and methods by which a change in ameasurement and or reference beam path may be quickly measured and usedin contemporaneous applications or in non-contemporaneous applicationswherein either or both the optical properties of a gas in themeasurement path and/or the physical length of the measurement path maybe changing. An example of a contemporaneous application is in aninterferometric angle and/or distance measuring instrument to enhanceaccuracy by compensating for gas turbulence and acoustic perturbationeffects on the optical properties of the gas in the measurement and/orreference beam paths, especially changes in the measurement andreference beam paths that take place during the measuring period becauseof gas turbulence and acoustic perturbation effects induced in themeasurement and reference beam paths by rapid stage slew rates. Anexample of a non-contemporaneous application is an interferometric angleand/or linear displacement measuring instrument to enhance accuracy ofcompensating for gas turbulence and acoustic perturbation effects indetermination of alignment mark locations.

Non-dispersive interferometry used for the compensation of certain ofthe effects of a gas in the measurement and/or reference beam paths isbased on interferometric measurements using measurement beams includinga single optical wavelength. The non-dispersive techniques are based onthe measurement of effects of the gas on the optical path lengthexperienced by a beam.

FIG. 2 a shows an embodiment of a multiple measurement beam paths planemirror interferometer 100 that measures the effects of the gas on theoptical path length experienced by a beam. The interferometer directsmultiple measurement beams to each contact a measurement object 120three or more times. For example, the measurement object may be a stagemirror for a wafer stage in a microlithography system. Interferometer100 produces multiple output beams 124A, 124B, 130A, and 130B eachincluding interferometric information about changes in distance betweenthe interferometry system and the measurement object along acorresponding measurement axis, changes in orientation of themeasurement object, and effects of turbulence and acoustic perturbationson the multiple output beams.

Interferometer 100 has the property that the output beams each includesa measurement component that makes at least two passes to themeasurement object before being detected or before being directed alongseparate measurement beam paths for a third pass to the measurementobject. Accordingly, the interferometer is similar to those disclosed incommonly owned U.S. Pat. No. 6,819,434 B2 by Henry, A. Hill and entitled“Multiple Degree Of Freedom Interferometer.” The contents of U.S. Pat.No. 6,819,434 B2 are incorporated herein in their entirety by reference.Interferometer 100 is different from those disclosed in the referencedpatent in that it provides two interferometric signals for each of oneor more measurement axes, a feature that can be used to provide gasturbulence and acoustic perturbation information for respectivemeasurement beam paths and surface information about the measurementobject independent of its angular orientation.

Interferometer 100 is also different from those disclosed in commonlyowned U.S. Pat. No. 6,757,066 entitled “Multiple Degree Of Freedom HighStability Plane Mirror Interferometer;” U.S. Provisional PatentApplication No. 60/534,481 entitled “Multi-Axis Interferometer ForMirror Mapping,” No. 60/535,078 entitled “Multi-Axis Interferometer ForMirror Mapping,” No. 60/564,448 entitled “Multi-Axis Interferometer AndData Processing For Mirror Mapping,” and No. 60/644,898 entitled“Multi-Axis Interferometer And Data Processing For Mirror Mapping;” andU.S. patent application Ser. No. 11/030,755 entitled “Multi-AxisInterferometer For Mirror Mapping,” Ser. No. 11/112,375 entitled“Multi-Axis Interferometer And Data Processing For Mirror Mapping,” andSer. No. 11/112,681 entitled “Multi-Axis Interferometer And DataProcessing For Mirror Mapping.” The provisional application No.60/564,448 and No. 60/644,898 and the utility application Ser. No.11/112,375 and Ser. No. 11/112,681 are by Henry A. Hill and Gary Womackand the remaining cited patent, provisional applications, and utilityapplications are by Henry A. Hill. The contents of the cited patent,provisional applications, and the utility applications are herebyincorporated herein in their entirety by reference. The interferometersdescribed in cited patent, provisional applications, and the utilityapplications are different from interferometer 100 in that they providethree measurement axes in a common plane and the first pass measurementbeam for each of the three axes is a common beam.

In the described embodiment, interferometer 100 includes a beamconditioning section and two single pass plane mirror interferometerswherein the measurement axes of the two single pass plane mirrorinterferometers are parallel and lie in a common vertical plane. The twosingle pass plane mirror interferometers comprise polarizingbeam-splitters 160A and 160B, half-wave phase retardation plates 170Dand 170E, retroreflector 162, and quarter-wave phase retardation plate170F. The two output beams from the two single pass plane mirrorinterferometers are 130A and 130B. The beam conditioning sectioncomprises polarizing beam-splitters 142 and 156; afocal systemsincluding anamorphic prisms 144A, 144B, 148A, 148B, 152A, and 152B; aretroreflector including elements 146A and 146B, and aperture mask 154.

There are six measurement beams that contact measurement object 150 atspots 132A, 134A, and 136A and at spots 132B, 134B, and 136B. Themeasurement beams associated with elliptical spots 132A, 134A, and 136Aare derived from input beam component 112A and measurement beam spots132B, 134B, and 136B are derived from input beam 112B. The design of thebeam conditioning in the vertical direction in interferometer 100 issuch that spots 132A, 134B, and 136A lie in one horizontal line andspots 132B, 134A, and 136B lie is a second horizontal line. This isachieved in interferometer 100 with optical elements as shown in FIG. 2a and an additional Rhomb (not shown in FIG. 2 a) placed to introduce avertical displacement of beams, e.g., placed in the paths of beams 116Aand 116B, in the paths of beams 118A and 118B, or between the setanamorphic prism elements 152A and 152B and aperture mask 154. Thevertical separation between the top row of spots 132A, 134B, and 136Aand the bottom row of spots 132B, 134A, and 136B is b (see FIG. 2 b). bmay be relatively small (e.g., on the order of one or two centimeters),allowing a relatively narrow mirror to be used for plane stage mirror50. In the described embodiment, the six spots are arranged in threevertical columns. However, the six spots may be arranged in some othergeometric pattern depending on, for example, expected gas flow or stagemirror shape in the system. The shape of spots 132A, 134A, and 136A andspots 132B, 134B, and 136B are elliptical in cross-section so as tominimize the effects of beam shears introduced by changes in orientationof measurement object 150.

Continuing with the description, interferometer 100 includes apolarizing beam splitter 140 which splits an input beam 110 includingtwo orthogonally polarized components with a difference in frequenciesof ω_(R) into first and second measurement components 112A and 112B,respectively. Interferometer 100 also includes half-wave phaseretardation plate 170A which rotates the plane of polarization ofmeasurement beam 112A by 90° such that first and second measurementbeams 112A and 112B are in the same polarization state. First and secondmeasurement beams 112A and 112B are reflected by polarizing beamsplitter 142 as first and second measurement beams 114A and 114B,respectively. Interferometer 100 directs first and second measurementbeams 114A and 114B along paths that contact measurement object 150 atdifferent locations in a vertical or z direction at spots 132A and 132B,respectively.

Interferometer 100 also includes quarter-wave phase retardation plate170B which is located between polarizing beam splitter 142 andmeasurement object 150. Quarter-wave phase retardation plate 170Brotates by 90° the polarization states of double passed beams directedbetween the polarizing beam splitter 142 and measurement object 150.Accordingly, polarizing beam splitter 170B transmits an out-going beamthat would have been reflected in its incoming polarization state.

The direction of propagation of components of measurement beams 114A and114B reflected by measurement object 150 is changed by pitch and yawangles 2θ_(P) and 2θ_(Y) for a change in orientation of measurementobject 150 by pitch and yaw angles θ_(P) and θ_(Y), respectively.Measurement beams 114A and 114B reflected by measurement object 150 arenext transmitted by polarizing beam-splitter 142 and anamorphic prisms144A and 144B as yaw expanded measurement beams 116A and 116B,respectively. The magnification η_(Y) in the yaw plane is selected suchthatη_(Y)=2.  (1)Accordingly, the direction of propagation θ′_(Y) of measurement beams116A and 116B in the yaw direction is

$\begin{matrix}\begin{matrix}{\vartheta_{Y}^{\prime} = {\left( \frac{2}{\eta_{Y}} \right)\vartheta_{Y}}} \\{= {\vartheta_{Y}.}}\end{matrix} & (2)\end{matrix}$

Yaw expanded measurement beams 116A and 116B are next reflected as yawexpanded measurement beams 118B and 118A, respectively, by aretroreflector including elements 146A and 146B. Retroreflectorincluding elements 146A and 146B is shown in FIG. 2 a as a polarizationpreserving retroreflector such as described in U.S. Pat. No. 6,198,574B1 entitled “Polarization Preserving Optical Systems” and U.S. Pat. No.6,201,609 B1 entitled “Interferometers Utilizing Polarization PreservingOptical Systems.” Both of the two cited patents are by Henry A. Hill andthe contents thereof are incorporated in their entirety by reference.Other types of retroreflectors may be used in embodiments of the presentinvention, e.g., a corner cube retroreflector, without departing fromthe scope and spirit of the present invention. Retroreflectors 146A and146B can invert the positions of beams 116A and 116B with respect to thez-axis.

Yaw expanded measurement beams 118B and 118A are next expanded in thepitch direction as pitch and yaw expanded measurement beamscorresponding to beams 120B and 120A, respectively, by anamorphic prisms148A and 148B and anamorphic prisms 152A and 152B. The magnificationη_(P) in the pitch plane is selected such thatη_(P)=2.  (3)Accordingly, the direction of propagation θ′_(P) of expanded measurementbeams corresponding to beams 120B and 120A in the pitch direction is

$\begin{matrix}\begin{matrix}{\vartheta_{P}^{\prime} = {\left( \frac{2}{\eta_{P}} \right)\vartheta_{P}}} \\{= {\vartheta_{P}.}}\end{matrix} & (4)\end{matrix}$

As a consequence of the conditions set out in Eqs. (2) and (4), thedirection of propagation of expanded measurement beams corresponding tobeams 120B and 120A are always perpendicular to the surface of planemeasurement object 150 independent of changes in orientation ofmeasurement object 150.

The expanded measurement beams 120B and 120A correspond to portions ofcorresponding expanded measurement beams transmitted by anamorphicprisms 152A and 152B, respectively. Aperture mask 154 comprises to twoapertures that are elliptical in cross-section to generate theelliptical cross-sectional shape of spots 134B, 134A, 136A, and 136B andthe demagnified elliptical cross-sectional shape of conjugate imagespots 132A and 132B. As a result of aperture mask 154, there is no beamshear of measurement beams 120B and 120A at aperture mask 154.

In the last step of the beam conditioning section of interferometer 100,measurement beams 120B and 120A each make a single pass to measurementobject 150 as measurement beams 122B and 122A, respectively, to formspots 134B and 134A, respectively. Components of measurement beams 122Band 122A are incident on measurement object 150 with zero values forrespective angles of incidence.

The pitch and yaw beam shears s_(P,2) and s_(Y,2), respectively, ofmeasurement beams 122B and 122A at spots 134B and 134A are given by theformulas_(P,2)=θ_(P)L,s_(Y,2)=θ_(Y)L  (5)where L is the one way physical path length of measurement beams 122Band 122A. Note that the beam shears expressed by Eq. (5) is ¼ of thecorresponding beam shears experienced in for example a HSPMI.

The respective components of beams 122B and 122A are parallel because ofthe zero angle of incidence of components of beams 122B and 122A atmeasurement object 150. The components of beams 122B and 122A incidenton polarizing beam-splitter 156 are reflected as a result of the doublepass through quarter-wave phase retardation plate 170C. The reflectedcomponents of beams 122B and 122A are incident on a retroreflectorincluding elements 158A and 158B. The description of retroreflectorincluding elements 158A and 158B is the same as the description givenfor retroreflector including elements 146A and 146B.

A first portions of reflected components of beams 122B and 122A incidenton the retroreflector including elements 158A and 158B are transmittedby non-polarizing beam-splitter 172 as beams 124A and 124B,respectively. Beams 124A and 124B are subsequently combined as a mixedbeam and detected to generate the first electrical interference signalS₁.

The frequency domains of the stationary non-random effects of a gas andother gas related effects generally fall into separated regions. Forturbulence effects, the corresponding frequency domain is generallydetermined by dimensions of turbulent cells and the speed of transportof the cells through the measurement and/or reference beam paths. Forthe example of a turbulence generated cell with a characteristicdimension of 0.04 m and an gas flow speed perpendicular to the axes ofthe measurement and/or reference beam paths of 0.2 m/s, thecorresponding frequency is of the order of 5 Hz.

The frequency domain of stationary non-random effects is determined bythe frequency spectrum of velocity profile of a scanning stage. Acharacteristic frequency of the frequency spectrum is the inverse of thetime to scan a single die site on a wafer, e.g., 10 Hz.

The frequency domain of vibrations is determined by the resonantfrequencies of different components of a lithographic tool including themetrology system used to measure the position of the respective stage.

The frequency domain of an acoustic perturbation except for an acousticpulse generated by an acceleration of a measurement object will bedetermined primarily by the normal mode spectrum of a cavity containinginterferometer system 15. For the example of interferometer system 15located in a lithography tool with characteristic dimensions of 1.5 m,the normal mode spectrum of the lithography tool will comprise afundamental mode with a frequency of approximately 200 Hz and harmonicmodes thereof. Environmental effects of the gas generally generatechanges in the optical path lengths with frequencies approximately 1 Hz.

The phase Φ₁ of electrical interference signal S₁ is independent oflinear displacements of measurement object 150, is sensitive to angulardisplacements in pitch of measurement object 150, is sensitive to gasturbulence and acoustic perturbation effects in second and higher orderspatial derivatives, and is sensitive to second and higher order spatialderivatives of the surface figure of measurement object 150 as expressedby the following equation,

$\begin{matrix}{\Phi_{1} = {k\left\{ {{b\;\vartheta_{P}} + {4\left( \frac{b}{2} \right)\left( \frac{c}{2} \right)\left( {\frac{\partial}{\partial x}\frac{\partial}{\partial z}} \right)\left( {\zeta_{1,2} + \xi_{1,2}} \right)}} \right\}}} & (6)\end{matrix}$where k is the wavenumber of the respective measurement beams; c is thehorizontal spacing of spots 132A, 132B, 134B, and 134A; ζ_(1,2)represents the effects of gas turbulence and acoustic perturbationsalong an axis defined by measurement beams 114A, 114B, 122B, and 122A;and ξ_(1,2) represents the effects of surface figure errors ofmeasurement object 150 at a spot defined by the location of spots 132A,132B, 134B, and 134A. Note that there are no first order spatialderivatives of ζ_(1,2) and ξ_(1,2) present in Eq. (6) as a result of thedesign of interferometer 100 that places spots 132A and 134B in onehorizontal line and spots 132B and 134A in a second horizontal line.

It is evident on examination of Eq. (6) that a measurement of the changein pitch of measurement object 150 is obtained from measurements of Φ₁that is compensated for effects of gas turbulence and acousticperturbation effects up through first order spatial derivatives of thegas turbulence and acoustic perturbation effects. It is also evident onexamination of Eq. (6) that a measurement of the change in pitch ofmeasurement object 150 is obtained from measurements of Φ₁ that iscompensated for effects errors in the surface figure of measurementobject 150 up through first order spatial derivatives of the surfacefigure errors.

A second portions of reflected components of beams 122B and 122Aincident on the retroreflector including elements 158A and 158B arereflected by non-polarizing beam-splitter 172 as measurement beamsincident on half-wave phase retardation plate 170D. Half-wave phaseretardation plate 170D is oriented so as to rotate the plane ofpolarizations of the second portions of reflected components of beams122B and 122A by 45°.

A first portions of the second portions of reflected components of beams122B and 122A are transmitted by polarizing beam-splitter 160A and aretroreflector 162 as reference beams 128A and 128B. The description ofretroreflector 162 is the same as the description given for theretroreflector including elements 146A and 146B. A second portions ofthe second portions of reflected components of beams 122B and 122A arereflected by polarizing beam-splitter 160A and transmitted by polarizingbeam-splitter 160B as measurement beams 126A and 126B. Measurement beams126A and 126B are transmitted by polarizing beam-splitter 160B as aresult of passing through half-wave phase retardation plate 170E whichis oriented so as to rotate the plane of polarization of the respectivebeams by 90°.

The shear of reference beams 128A and 128B and measurement beams 126Aand 126B at polarizing beam-splitter 160B is reduced because of theshort path length between beam-splitter 160B and aperture mask 154 andbecause of the reduced magnitude of the changes in the directions ofpropagation of the respective beams. The shear of measurement beams 126Aand 126B at measurement object 150 is the same as given by Eq. (5). Noteagain that the beam shears for measurement beams 126A and 126B atmeasurement object 150 is ¼ of the corresponding beam shears experiencedin for example a HSPMI.

The components of measurement beams 126A and 126B incident on polarizingbeam-splitter 160B are reflected after a double pass throughquarter-wave phase retardation plate 170F as measurement beam componentsof output beams 130A and 130B, respectively. Reference beams 128A and128B are transmitted by polarizing beam-splitter 160B as reference beamcomponents of output beams 130B and 130A, respectively. The componentsof output beams 130A and 130B are subsequently mixed and detected aselectrical interference signals S₅ and S₆, respectively.

The phases Φ₅ and Φ₆ of electrical interference signals S₅ and S₆,respectively, contain information about the displacement of measurementobject 150, about the effects of gas turbulence and acousticperturbation effects, and about errors in the surface figure ofmeasurement object 150 according to the following equations.Φ₅=2k(L+ζ ₅+ξ₅)+kbθ _(P),  (7)Φ₆=2k(L+ζ ₆+ξ₆)−kbθ _(P)  (8)where ζ₅ and ζ₆ represents the effects of gas turbulence and acousticperturbations along the paths of measurement beams 126A and 126B,respectively, and ξ₅ and ξ₆ represents the effects of surface figureerrors of measurement object 150 at the location of spots 136A and 136B,respectively.

The difference in phases Φ₅−Φ₆ is next computed to generate a firstdifference parameter (FDP),Φ₅−Φ₆=2kbθ _(P) +k(ζ₅−ζ₆)+(ξ₅−ξ₆).  (9)The average of Φ₅−Φ₆ is used to obtain information in situ about theeffects of surface figure errors of measurement object 150 at thelocation of spots 136A and 136B, respectively. The phase differenceΦ₅−Φ₆ compensated for the measured effects of surface figure errors ofmeasurement object 150 and compensated for changes in pitch using theresults of measured values of Φ₁ are inverted to obtain a value for theaverage value of (ζ₅+ζ₆). The average value of (ζ₅+ζ₆) is subsequentlyused to compensate for effects of gas turbulence and acousticperturbation effects in the measured value of the displacement ofmeasurement object 150 from the sum (Φ₅+Φ₆).

While interferometer 100 as shown in FIG. 2 a is a threedegree-of-freedom interferometer, other configurations are alsopossible. For example, in some embodiments, interferometer 100 can beconfigured as a five-axis interferometer. Referring to FIG. 3 a,interferometer 100 can include a second set of the two single pass planemirror interferometers. The second set of interferometers includepolarizing beam-splitters 1160A and 1160B, half-wave phase retardationplates 1170D and 1170E, retroreflector 1162, and quarter-wave phaseretardation plate 1170F. The two output beams from the second set of twosingle pass plane mirror interferometers are 1130A and 1130B.

Accordingly, and with reference to FIG. 3 b, there are eightmeasurement/reference beams that contact measurement/reference object150 at spots 132A, 134A, 136A, and 1136A and at spots 132B, 134B, 136B,and 1136B. The measurement/reference beams associated with spots 132A,134A, 136A, and 1136A are derived from input beam component 112A andmeasurement/reference beam spots 132B, 134B, 136B, and 1136B are derivedfrom input beam 112B. The vertical separation between the top row ofspots 132A, 134B, 136A, and 1136A and the bottom row of spots 132B,134A, 136B, and 136B is b. In the described embodiment, the eight spotsare arranged in four vertical columns. However, the eight spots may bearranged in some other geometric pattern without departing from thescope and spirit of the present disclosure.

The shape of spots 132A, 134A, 136A, and 1136A and spots 132B, 134B,136B, and 1136B are elliptical in cross-section so as to minimize theeffects of beam shears introduced by changes in orientation ofmeasurement object 150 about the y direction (coordinate system used inFIG. 3 b).

For the second set of the two single pass interferometers, a secondportions of beams 124A and 124B are reflected by non-polarizingbeam-splitter 1162 as beams 1132A and 1132B, respectively, and beams1132A and 1132B are subsequently reflected by mirror 1164 as beams 1134Aand 1134B, respectively.

Beams 1124A and 1124B are mixed and detected as discussed for beams 124Aand 124B above.

Beams 1134A and 1134B are reflected by prism 1166 as measurement beamsincident on half-wave phase retardation plate 1170D. Half-wave phaseretardation plate 1170D is oriented so as to rotate the plane ofpolarizations of the second portions of reflected components of beams122B and 122A by 45°. A first portions of the beams incident onhalf-wave phase retardation plate 1170D are transmitted by polarizingbeam-splitter 1160A and a retroreflector 1162 as reference beams 1128Aand 1128B, respectively. The description of retroreflector 1162 is thesame as the description given for the retroreflector including elements146A and 146B. A second portions of the beams incident on half-wavephase retardation plate 1170D are reflected by polarizing beam-splitter1160A and transmitted by polarizing beam-splitter 1160B as measurementbeams 1126A and 1126B, respectively. Measurement beams 1126A and 1126Bare transmitted by polarizing beam-splitter 1160B as a result of passingthrough half-wave phase retardation plate 170E which is oriented so asto rotate the plane of polarization of the respective beams by 90°.

The shear of reference beams 1128A and 1128B and measurement beams 1126Aand 1126B at polarizing beam-splitter 1160B is reduced because of theshort path length between beam-splitter 1160B and aperture mask 154 andbecause of the reduced magnitude of the changes in the directions ofpropagation of the respective beams. The shear of measurement beams1126A and 1126B at measurement object 150 is the same as given by Eq.(5). Note again that the beam shears for measurement beams 1126A and1126B at measurement object 150 is ¼ of the corresponding beam shearsexperienced in for example a HSPMI.

The components of measurement beams 1126A and 1126B incident onpolarizing beam-splitter 1160B are reflected after a double pass throughquarter-wave phase retardation plate 1170F as measurement beamcomponents of output beams 1130A and 1130B, respectively. Referencebeams 1128A and 1128B are transmitted by polarizing beam-splitter 1160Bas reference beam components of output beams 1130B and 1130A,respectively. The components of output beams 1130A and 1130B aresubsequently mixed and detected as electrical interference signals S₇and S₈, respectively. The detectors include analyzers to mixpolarization components of output beams

Phases Φ₇ and Φ₈ of electrical interference signals S₇ and S₈,respectively, contain information about the displacement of measurementobject 150; about the stationary non-random effects of the gas and theother related effects of the gas along measurement paths x₇ and x₈,respectively; and about errors in the surface figure of measurementobject 150 according to the following equations.Φ₇=2k(x ₇+ζ₇+ξ₇)+2kbθ _(P),  (10)Φ₈=2k(x ₈+ζ₈+ξ₈)−2kbθ _(P)  (11)where ζ₇ and ζ₈ represent the stationary non-random effects of the gasand the other related effects of the gas along the x₇ and x₈ paths,respectively, of measurement beams 1126A and 1126B, respectively, and ξ₇and ξ₈ represent the effects of surface figure errors of measurementobject 150 at the location of spots 1136A and 1136B, respectively.

The difference in phases Φ₇−Φ₈ is next computed to subsequently generatea quantity related to a FDP,Φ₇−Φ₈=4kbθ _(P)+2k(ζ₇−ζ₈)+2k(ξ₇−ξ₈).  (12)

The average of Φ₇−Φ₈ is used to obtain information in situ about theeffects of surface figure errors of measurement object 150 at thelocation of spots 136A and 136B, respectively. The phase differenceΦ₇−Φ₈ compensated for the measured effects of surface figure errors ofmeasurement object 150 and compensated for changes in pitch using theresults of measured values of Φ₁ are inverted to obtain a value for theaverage value of (ζ₇+ζ₈). The average value of (ζ₇+ζ₈) is subsequentlyused to compensate for stationary non-random effects of the gas and theother related effects of the gas effects in the measured value of thedisplacement of measurement object 150 from the sum (Φ₇+Φ₈).

Measurement of pitch is obtained using Eq. (6). Measurements of thestationary non-random effects of the gas and the other related effectsof the gas are obtained from the inversions of Eqs. (9) and (12) assubsequently described herein and compensation for the pitchcontribution using the measured value of pitch. Measurement of thelinear displacement is obtained from the average of the lineardisplacements x₅, x₆, x₇, and x₈ obtained from Eqs. (7), (8), (10), and(11) after compensation for the contributions of the stationarynon-random effects of the gas and the other related effects of the gasusing the measured values of the stationary non-random effects of thegas and the other related effects of the gas, compensation for the pitchterm using the measured value of pitch and the beam spacing parameter b.Measurement of yaw is obtained from the difference of the average valueof x₅ and x₆ and the average value of x₇ and x₈ compensated for thecontributions of the stationary non-random effects of the gas and theother related effects of the gas using the measured values of thestationary non-random effects of the gas and the other related effectsof the gas, and beam spacing parameter c (see FIG. 3 b).

In general, values of a FDP can be measured by interferometer 100 eitherduring the normal processing cycle of wafers and/or during periods otherthan a normal processing cycle of wafers, such as during aninitialization or setup procedure.

In some embodiments, improved statistical accuracy in measured values ofFDP can be obtained by taking advantage of the relatively low bandwidthof measured values of FDP compared to the bandwidth of the correspondinglinear displacement measurements using averaging or low pass filtering.

In some embodiments, non-stationary non-random effects and the otherrelated effects of the gas can be described mathematically byrepresenting the non-stationary non-random effects as an ensemble ofcells of gas and acoustic perturbations that move and propagate,respectively, through the measurement paths of beams 114A, 114B, 122A,122B, 126A, 126B, 1126A, and 1126B in interferometer 100. The spatialdistribution of cell or perturbation m of refractivity[n(x,y,z,t)−1]_(T) is represented by a function ƒ_(m)(x,y,z,t) such that

$\begin{matrix}\begin{matrix}{\zeta_{i}^{\prime} = {\int_{x_{i}^{\prime}}{\left\lbrack {{n\left( {x_{i}^{\prime},y,z,t} \right)} - 1} \right\rbrack_{T}{\mathbb{d}x_{i}^{\prime}}}}} \\{= {\int_{x_{i}^{\prime}}{\left\lbrack {\sum\limits_{m = 1}{f_{m}\left( {x_{i}^{\prime},y,z,t} \right)}} \right\rbrack{{\mathbb{d}x_{i}^{\prime}}.}}}}\end{matrix} & (13)\end{matrix}$

Representation of the integration over the respective areas of beams114A, 114B, 122A, 122B, 126A, 126B, 1126A, and 1126B in Eq. (13) issuppressed. Function ƒ_(m)(x′_(i),y,z,t) may vary from cell to cell orfrom perturbation to perturbation. A cell may represent the effect of anon-uniform composition of the gas or the effect of a turbulent eddy.

Inversion of Gas Stationary Non-Random Effects and Other RelatedEffects: Fourier Series Inversion Techniques

The first difference parameter FDP_(j,j+1), j=5, 7, given by Eq. (9) canbe written in terms of stationary non-random effects of the gas and theother related effects of the gas ζ′_(i), i=5, 6, 7, and 8, asFDP_(j,j+1)=ζ′_(j)(t)−ζ′_(j+1)(t), j=5,7.  (14)

The technique for inversion of stationary non-random effects of the gasand the other related effects of the gas is based on application ofFourier series techniques. Inversion of FDP_(j,j+1)(t) may also beachieved by digital integration and Fourier transform techniques such asdescribed in referenced U.S. patent application Ser. No. 6,839,141 B2,Ser. No. 10/701,759, and Ser. No. 11/413,917 and U.S. ProvisionalApplication No. 60/862,949. The Fourier series techniques are furtherdescribed herein.

For a time period covering a time domain T

$\begin{matrix}{{{\zeta_{j,{j + 1}}^{\prime}(t)} = {{\sum\limits_{m = 1}^{N}\;{A_{m}{\cos\left\lbrack {m\; 2\;\pi\frac{\left( {t - \overset{\_}{t}} \right)}{T}} \right\rbrack}}} + {\sum\limits_{m = 1}^{N}\;{B_{m}{\sin\left\lbrack {m\; 2\;\pi\frac{t - \overset{\_}{t}}{T}} \right\rbrack}}}}},{{- \frac{1}{2}} \leq \frac{\left( {t - \overset{\_}{t}} \right)}{T} \leq \frac{1}{2}},{j = 5},7} & (15)\end{matrix}$where τ can in general will be a function of time, t is the averagevalue of time t over the time domain (t−T) to t, and N is an integerdetermined by consideration of the temporal frequencies that are to beincluded in the series representation. A constant value is omitted fromEq. (15) since the average value of ζ′_(i) should statistically be zero.There will be a low frequency contribution to ζ′_(i) from environmentaleffects which can be measured for example by an array of wavelengthmonitors.

Using the definition of FDP_(j,j+1) given by Eq. (14), the correspondingseries for FDP_(j,j+1) is next written as

$\begin{matrix}{{{{FDP}_{j,{j + 1}}(t)} = {{2{\sum\limits_{m = 1}^{N}\;{B_{m}{\sin\left( {m\;\pi\frac{\tau}{T}} \right)}{\cos\left\lbrack {m\; 2\;\pi\frac{\left( {t - \overset{\_}{t}} \right)}{T}} \right\rbrack}}}} - {2{\sum\limits_{m = 1}^{N}\;{A_{m}{\sin\left( {m\;\pi\;\frac{\tau}{T}} \right)}{\sin\left\lbrack {m\; 2\;\pi\frac{\left( {t - \overset{\_}{t}} \right)}{T}} \right\rbrack}}}}}},{{- \frac{1}{2}} \leq \frac{\left( {t - \overset{\_}{t}} \right)}{T} \leq \frac{1}{2}},{j = 5},7.} & (16)\end{matrix}$

A contracted form of Eq. (16) is obtained with the introduction ofA_(m)′ and B_(m)′ as

$\begin{matrix}{{{{{FDP}_{j,{j + 1}}(t)} = {\sum\limits_{m = 1}^{N}\;\left\{ {{A_{m}^{\prime}{\cos\left\lbrack {m\; 2\;\pi\frac{\left( {t - \overset{\_}{t}} \right)}{T}} \right\rbrack}} + {B_{m}^{\prime}{\sin\left\lbrack {m\; 2\;\pi\frac{\left( {t - \overset{\_}{t}} \right)}{T}} \right\rbrack}}} \right\}}},{{- \frac{1}{2}} \leq \frac{\left( {t - \overset{\_}{t}} \right)}{T} \leq \frac{1}{2}},{j = 5},7}{where}} & (17) \\{{A_{m}^{\prime} = {\int_{\frac{({t^{\prime} - \overset{\_}{t}})}{T} = {- \frac{1}{2}}}^{\frac{({t^{\prime} - \overset{\_}{t}})}{T} = \frac{1}{2}}{\frac{2}{T}{{FDP}_{j,{j + 1}}\left( t^{\prime} \right)}{\cos\left\lbrack {m\; 2\;\pi\frac{\left( {t^{\prime} - \overset{\_}{t}} \right)}{T}} \right\rbrack}{\mathbb{d}t^{\prime}}}}},{m > 0},{j = 5},{7;}} & (18) \\{{B_{m}^{\prime} = {\int_{\frac{({t^{\prime} - \overset{\_}{t}})}{T} = {- \frac{1}{2}}}^{\frac{({t^{\prime} - \overset{\_}{t}})}{T} = \frac{1}{2}}{\frac{2}{T}{{FDP}_{j,{j + 1}}\left( t^{\prime} \right)}{\sin\left\lbrack {m\; 2\;\pi\frac{\left( {t^{\prime} - \overset{\_}{t}} \right)}{T}} \right\rbrack}{\mathbb{d}t^{\prime}}}}},{m > 0},{j = 5},7.} & (19)\end{matrix}$

With the expressions for FDP_(j,j+1)(t) given by Eqs. (16) and (17),Eqs. (18) and (19) for A_(m)′ and B_(m)′, respectively, can be writtenin terms of A_(m) and B_(m) as

$\begin{matrix}{{A_{p}^{\prime} = {{\int_{\frac{({t - \overset{\_}{t}})}{T} \geq {- \frac{1}{2}}}^{\frac{({t - \overset{\_}{t}})}{T} \leq \frac{1}{2}}{2\;{\cos\left\lbrack {p\; 2\;\pi\frac{\left( {t - \overset{\_}{t}} \right)}{T}} \right\rbrack} \times {\sum\limits_{m = 1}^{N}\;{B_{m}{\sin\left( {m\;\pi\frac{\tau}{T}} \right)}{\cos\left\lbrack {m\; 2\;\pi\frac{\left( {t - \overset{\_}{t}} \right)}{T}} \right\rbrack}{\mathbb{d}t}}}}} - {\int_{\frac{({t - \overset{\_}{t}})}{T} \geq {- \frac{1}{2}}}^{\frac{({t - \overset{\_}{t}})}{T} \leq \frac{1}{2}}{2\;{\cos\left\lbrack {p\; 2\;\pi\frac{\left( {t - \overset{\_}{t}} \right)}{T}} \right\rbrack} \times {\sum\limits_{m = 1}^{N}\;{A_{m}{\sin\left( {m\;\pi\;\frac{\tau}{T}} \right)}{\sin\left\lbrack {m\; 2\;\pi\frac{\left( {t - \overset{\_}{t}} \right)}{T}} \right\rbrack}{\mathbb{d}t}}}}}}},{p > 0},} & (20) \\{{B_{p}^{\prime} = {{\int_{\frac{({t - \overset{\_}{t}})}{T} \geq {- \frac{1}{2}}}^{\frac{({t - \overset{\_}{t}})}{T} \leq \frac{1}{2}}{2\;{\sin\left\lbrack {p\; 2\;\pi\frac{\left( {t - \overset{\_}{t}} \right)}{T}} \right\rbrack} \times {\sum\limits_{m = 1}^{N}\;{B_{m}{\sin\left( {m\;\pi\frac{\tau}{T}} \right)}{\cos\left\lbrack {m\; 2\;\pi\frac{\left( {t - \overset{\_}{t}} \right)}{T}} \right\rbrack}{\mathbb{d}t}}}}} - {\int_{\frac{({t - \overset{\_}{t}})}{T} \geq {- \frac{1}{2}}}^{\frac{({t - \overset{\_}{t}})}{T} \leq \frac{1}{2}}{2\;{\sin\left\lbrack {p\; 2\;\pi\frac{\left( {t - \overset{\_}{t}} \right)}{T}} \right\rbrack} \times {\sum\limits_{m = 1}^{N}\;{A_{m}{\sin\left( {m\;\pi\;\frac{\tau}{T}} \right)}{\sin\left\lbrack {m\; 2\;\pi\frac{\left( {t - \overset{\_}{t}} \right)}{T}} \right\rbrack}{\mathbb{d}t}}}}}}},{p > 0.}} & (21)\end{matrix}$

Eqs. (20) and (21) can be written in the contracted matrix form

$\begin{matrix}{\begin{pmatrix}A_{1}^{\prime} \\\vdots \\A_{N}^{\prime} \\B_{1}^{\prime} \\\vdots \\B_{N}^{\prime}\end{pmatrix} = {\left( M_{n,m} \right)\begin{pmatrix}A_{1} \\\vdots \\A_{N} \\B_{1} \\\vdots \\B_{N}\end{pmatrix}}} & (22)\end{matrix}$where the matrix elements M_(n,m) of matrix (M_(n,m)) are given bycorresponding factors in Eqs. (20) and (21).

For the situation where the deviation of τ from an average value τ is asmall fraction of τ, i.e., |τ− τ|/ τ<<1, the off diagonal matrixelements of matrix (M_(n,m)) are in general small compared to thecorresponding diagonal matrix elements. In the case where the offdiagonal matrix elements can be neglected, the matrix transformationexpressed by Eq. (22) can be written in another contracted form whereA_(p)′ and B_(p)′ are obtained from A_(p) and B_(p) by a complexrotation operator T. Complex rotation or transfer operator T has realand imaginary components Re(T_(p)) and Im(T_(p)) where

$\begin{matrix}{{A_{p}^{\prime} = {{T_{p}}\left\lbrack {{A_{p}\cos\;\vartheta} + {B_{p}\sin\;\vartheta}} \right\rbrack}},} & (23) \\{{B_{p}^{\prime} = {{T_{p}}\left\lbrack {{{- A_{p}}\sin\;\vartheta} + {B_{p}\cos\;\vartheta}} \right\rbrack}},} & (24) \\{{\tan\;\vartheta} = {\frac{{Im}\left( T_{p} \right)}{{Re}\left( T_{p} \right)}.}} & (25)\end{matrix}$

The real and imaginary components Re(T_(p)) and Im(T_(p)) are given bythe formulae

$\begin{matrix}{{{{Re}\left( T_{p} \right)} = 0},{p > 0},} & (26) \\{{{{Im}\left( T_{p} \right)} = {2\;{\sin\left( {p\;\pi\frac{\tau}{T}} \right)}}},{p > 0.}} & (27)\end{matrix}$

The first zero in |T_(p)| beyond the zero at p=0 occurs at p=250. ForT=5 sec and τ=20 msec for a beam spacing b=0.006 m and a speed of gasflow of 0.3 m/sec, the frequency ω/2π=p(1/T) is 50 Hz. at p=250 which islocated in between typical values of frequency domains of the stationarynon-random effects of the gas and the other related effects. The maximumvalue of the location of the first zero in |T_(p)| beyond the zero atp=0 is determined by the maximum value of the vertical beam spacing fora given gas flow pattern.

Enhanced FDP_(j,j+1) Sensitivity at Low Frequencies

The sensitivity of FDP_(j,j+1) at low frequencies is increased indisclosed embodiments by a technique related to a discrete integrationtechnique described in referenced U.S. patent application Ser. No.10/701,759. The discrete integration technique takes advantage of thetemporal properties of ζ_(j)(t) relative to ζ_(j+1)(t+τ), j=5, 7, i.e.,ζ_(j)(t)≅ζ_(j+1)(t+τ), j=5, 7. This property is used in embodiments toincrease the effective spacing between beams x_(j) and x_(j+1), j=5, 7,from b to qb where q=2, 3, . . . . The corresponding value forFDP_(j,j+1)(t,qτ) is given by the following formula

$\begin{matrix}{{{FDP}_{j,{j + 1}}\left( {t,{qb}} \right)} = {\sum\limits_{p = 0}^{q}\;{{{FDP}_{j,{j + 1}}\left( {t + {p\;\tau}} \right)}.}}} & (28)\end{matrix}$

The first difference parameter FDP_(j,j+1)(t,qτ) is to a goodapproximation equal to the first difference parameter that would beobtained by interferometer 100 shown in FIGS. 2 a and 2 b where thespacing b has been replaced by the spacing qb.

Elimination of Effects of Gibbs Phenomenon

The effects of the Gibbs phenomenon associated with a discontinuity whenusing a Fourier series representation [see Section 14.5 entitled “GibbsPhenomenon” in the book by G. Arfken Mathematical Methods ForPhysicists, Academic Press (1966)], may eliminated in disclosedembodiments by either of two related procedures. The two relatedprocedures add a function g_(i)(t), i=1, 2, to the measured values ofFDP_(j,j+1) to remove one or more discontinuities that may occur in themeasured values of FDP_(j,j+1) and temporal derivatives of FDP_(j,j+1)at the limits of time domain −1/2≦(t− t)/T≦1/2. In the first relatedprocedure, function g₁(t) is selected such that

$\begin{matrix}{{{\frac{d^{p}}{{dt}^{p}}\left\lbrack {{{FDP}_{j,{j + 1}}(t)} + {g_{1}(t)}} \right\rbrack}_{{t/T} = {1/2}} = {\frac{d^{p}}{{dt}^{p}}\left\lbrack {{{FDP}_{j,{j + 1}}(t)} + {g_{1}(t)}} \right\rbrack}_{{t/T} = {{- 1}/2}}},{p \geq 0}} & (29)\end{matrix}$so as to remove one or more discontinuities that may occur in themeasured values of FDP_(j,j+1) and temporal derivatives of FDP_(j,j+1)at the limits of time domain −1/2≦(t− t)/T≦1/2. A polynomial is chosenfor the functional form of g₁(t) in disclosed embodiments because theinversion of the respective g₁(t) is easily obtained with effects of theGibbs phenomenon compensated which is subsequently described herein.However, other functional forms may be selected for function g₁(t) suchas orthogonal functions, e.g., Chebyshev polynomials, without departingfrom the spirit and scope of disclosed embodiments.

To compensate for discontinuities up to the second temporal derivativesin FDP_(j,j+1), a third order polynomial is used for function g₁(t),i.e.,

$\begin{matrix}{{{g_{1}(t)} = {A + {B\left( \frac{t - \overset{\_}{t}}{T} \right)} + {\frac{1}{2!}{C\left( \frac{t - \overset{\_}{t}}{T} \right)}^{2}} + {\frac{1}{3!}{D\left( \frac{t - \overset{\_}{t}}{T} \right)}^{3}}}},} & (30)\end{matrix}$where A, B, C, and D are constants. The corresponding values forconstants A, B, C, and D for which the conditions of Eq. (29) aresatisfied are given by the formulae

$\begin{matrix}{{A = {{- {{FDP}_{j,{j + 1}}\left( \frac{1}{2} \right)}} - {\left( \frac{1}{2} \right)B} - {\left( \frac{1}{4} \right)C} - {\left( \frac{1}{8} \right)D}}},} & (31) \\{{B = {\left\lbrack {{- {{FDP}_{j,{j + 1}}\left( \frac{1}{2} \right)}} + {{FDP}_{j,{j + 1}}\left( {- \frac{1}{2}} \right)}} \right\rbrack - {\frac{1}{4!}\left\lbrack {{- {{FDP}_{j,{j + 1}}^{''}\left( \frac{1}{2} \right)}} + {{FDP}_{j,{j + 1}}^{''}\left( {- \frac{1}{2}} \right)}} \right\rbrack}}},} & (32) \\{{C = {\frac{1}{2}\left\lbrack {{- {{FDP}_{j,{j + 1}}^{\prime}\left( \frac{1}{2} \right)}} + {{FDP}_{j,{j + 1}}^{\prime}\left( {- \frac{1}{2}} \right)}} \right\rbrack}},} & (33) \\{D = {\frac{1}{3!}\left\lbrack {{- {{FDP}_{j,{j + 1}}^{''}\left( \frac{1}{2} \right)}} + {{FDP}_{j,{j + 1}}^{''}\left( {- \frac{1}{2}} \right)}} \right\rbrack}} & (34)\end{matrix}$where FDP_(j,j+1)′ and FDP_(j,j+1)″ correspond to the first and secondderivatives of FDP_(j,j+1), respectively, with respect to (t− t)/T.

The inverted value ζ′_(j,j+1,I) for ζ′_(j,j+1) is obtained using themeasured values of A_(m) and B_(m) in Eq. (15) as

$\begin{matrix}{{{\zeta_{j,{j + 1},I}^{\prime}(t)} = {{\sum\limits_{m = 1}^{N}\;{A_{m}{\cos\left\lbrack {m\; 2\;\pi\frac{\left( {t - \overset{\_}{t}} \right)}{T}} \right\rbrack}}} + {\sum\limits_{m = 1}^{N}\;{B_{m}{\sin\left\lbrack {m\; 2\;\pi\frac{\left( {t - \overset{\_}{t}} \right)}{T}} \right\rbrack}}} + {\left\langle {FDP}_{j,{j + 1}} \right\rangle{\left( \frac{T}{\tau} \right)\left\lbrack \frac{\left( {t - \overset{\_}{t}} \right)}{T} \right\rbrack}} - \left\{ {{{Inv}\left( g_{1} \right)} - {\left\langle g_{1} \right\rangle{\left( \frac{T}{\tau} \right)\left\lbrack \frac{\left( {t - \overset{\_}{t}} \right)}{T} \right\rbrack}} - \left\langle {{Inv}\left( g_{1} \right)} \right\rangle} \right\}}},{{- \frac{1}{2}} \leq \frac{\left( {t - \overset{\_}{t}} \right)}{T} \leq \frac{1}{2}},} & (35)\end{matrix}$where Inv(g₁) is obtained analytically from function g₁. Using theexpression for function g given by Eq. (30), the corresponding functionfor Inv(g₁) is given by the expression

$\begin{matrix}{{{{Invg}_{1}(t)}\; = {{A\left( \frac{t - \overset{\_}{t}}{T} \right)} + {B\left( \frac{t - \overset{\_}{t}}{T} \right)}^{2} + {\frac{1}{2!}{C\left( \frac{t - \overset{\_}{t}}{T} \right)}^{3}} + {\frac{1}{3!}{D\left( \frac{t - \overset{\_}{t}}{T} \right)}^{4}}}},} & (36)\end{matrix}$from represents the quantity obtained from the inversion of function g₁and

g₁

represents the average value of g₁ over the domain |t− t|≦1/2.

The function Inv(g₁) either represents the result obtained using theFourier series techniques described herein or the fit of a polynomial tothe result obtained using the Fourier series techniques described hereinwherein the order of the polynomial is one higher than the order of thepolynomial used for function g₁.

Higher order polynomials may also be used for function g₁(t). Inaddition, if only the effects of discontinuities in FDP_(j,j+1) up tothe first derivative need be eliminated, the value of constant D can beset equal to zero.

The second related procedure of the two related procedures forms anextended FDP, FDP^(E), and applies the first related procedure toextended FDP^(E). The extended FDP^(E) is defined as

$\begin{matrix}{{{FDP}_{j,{j + 1}}^{E}(t)} \equiv \left\{ \begin{matrix}{{{FDP}_{j,{j + 1}}\left\lbrack {\left( {t - \overset{\_}{t}} \right)/T} \right\rbrack},} & {{{- \frac{1}{2}} \leq \frac{\left( {t - \overset{\_}{t}} \right)}{T} \leq \frac{1}{2}},} \\{{- {{FDP}_{j,{j + 1}}\left\lbrack {1 - {\left( {t - \overset{\_}{t}} \right)/T}} \right\rbrack}},} & {\frac{1}{2} \leq \frac{\left( {t - \overset{\_}{t}} \right)}{T} \leq \frac{3}{2}}\end{matrix} \right.} & (37)\end{matrix}$where the second function g₂(t) is selected to make FDP_(j,j+1) ^(E)(t)continuous at (t− t)/T=1/2 to remove one or more discontinuities thatmay occur in the measured values of extended FDP_(j,j+1) ^(E)(t) andtemporal derivatives of extended FDP_(j,j+1) ^(E)(t) at the limits oftime domain −1/2≦(t− t)/T≦3/2.

The corresponding series for extended FDP_(j,j+1) ^(E)(t) is written as

$\begin{matrix}{{{{FDP}_{j,{j + 1}}^{E}(t)} = {{2{\sum\limits_{m = 1}^{N}\;{B_{m}{\sin\left( {m\;\pi\frac{\tau}{T}} \right)}{\cos\left\lbrack {m\; 2\;\pi\frac{\left( {t - \overset{\_}{t}} \right)}{T}} \right\rbrack}}}} - {2{\sum\limits_{m = 1}^{N}\;{A_{m}{\sin\left( {m\;\pi\frac{\tau}{T}} \right)}{\sin\left\lbrack {m\; 2\;\pi\frac{\left( {t - \overset{\_}{t}} \right)}{T}} \right\rbrack}}}}}},{{- \frac{1}{2}} \leq \frac{\left( {t - \overset{\_}{t}} \right)}{T} \leq \frac{3}{2}},{j = 5},7.} & (38)\end{matrix}$

The remaining description of the second related procedure is the same ascorresponding portions of the description given for the description ofthe first related procedure.

The advantage of the second related procedure is the all of thederivatives of extended FDP_(j,j+1) ^(E)(t) are continuous at (t−t)/T=1/2 by only requiring that extended FDP_(j,j+1) ^(E)(t) becontinuous at (t− t)/T=1/2. This leads to a simpler functional form forg₂(t) with improved results at the important end point (t− t)/T=1/2.

Systems Utilizing Reference Interferometers

In some embodiments, interferometry systems can include one or moreadditional interferometers along with a multi-axis interferometer. Forexample, referring to FIG. 4, in some embodiments, interferometer system15 includes interferometers 30 and 1010 mounted off-stage.Interferometer 30 is configured as a longitudinal referenceinterferometer (LRI) and interferometer 1010 is configured as a columnreference interferometer (CRI). LRI 30 includes an interferometer, e.g.,a high stability plane mirror interferometer (HSPMI), with fixedreference and measurement beam path lengths which are isolated fromnon-adiabatic changes in the optical properties of the gas. Other formsof a plane mirror configuration such as described in an article entitled“Differential interferometer arrangements for distance and anglemeasurements: Principles, advantages and applications” by C. Zanoni, VDIBerichte Nr. 749, pp 93-106 (1989) may be used for LRI 30 withoutdeparting from the scope and spirit of the present disclosure. Thecontents of the article by Zanoni are herein incorporated in theirentirety by reference.

CRI 1010 is configured to monitor the position of a fixed measurementobject 1050 with measurement beam 1012 and comprises an interferometer,e.g., a high stability plane mirror interferometer (HSPMI), with fixedreference and measurement path lengths. Measurement object 1050 isattached, for example, to the projection optic of the photolithographicapparatus. Other forms of a plane mirror configuration such as describedby Zanoni (supra) may be used for CRI 1010. In embodiments, CRI 1010 ispositioned sufficiently far from stage 16 so that the effects ofturbulence due to stage movement in negligible in interferometer path1012. In certain embodiments, CRI 1010 can be positioned relative to agas inlet or exhaust so that gas from the inlet or to the exhaust flowsthrough both interferometer path 1012 and path 12, introducingturbulence effects into measurements made using both interferometers 10and 1010.

Also mounted off-stage are interferometers 40 and 1020. Interferometer40 is configured as a LRI and interferometer 1020 is configured as aCRI. CRI 1020 is configured to monitor the position of a fixedmeasurement object 1060 with measurement beam 1022 and comprises aninterferometer, e.g., a HSPMI, with fixed reference and measurement pathlengths. Measurement object 1060 is attached for example to theprojection optic of the photolithographic apparatus. Other forms of aplane mirror configuration such as described by Zanoni (supra) may beused for CRI 1020 without departing from the scope and spirit of thepresent disclosure.

In some embodiments, LRIs 30 and 40 are wavelength monitors such asdescribed in commonly owned U.S. Pat. No. 4,685,803 and U.S. Pat. No.4,733,967. Both of the patents are by G. E. Sommargren and the contentsthereof are herein incorporated in their entirety by reference.

Two or more of interferometers 10, 20, 30, 40, 1010, and 1020 can usethe same light source for their respective input beams. In someembodiments, a single light source is used to provide input beams to allinterferometers.

Other configurations of interferometry systems are also possible. Forexample, while the system shown in FIG. 4 includes only two LRI's,systems can include more or fewer LRI's. For example, systems caninclude an array of several (i.e., more than two) LRI's, each configuredto provide information about adiabatic changes in the optical propertiesof the gas in the system for a variety of different positions in thelithography tool, providing additional information regarding theisotropy (or lack thereof) of the adiabatic changes.

In some embodiments, interferometer subsystems 10 and 20 can includeapparatus and methods of dispersive interferometry in combination withapparatus and methods of non-dispersive techniques for the compensationof effects of a dispersive medium such as a gas in the measurementand/or reference beam paths of the respective interferometer subsystems10 and 20. Interferometer subsystems 10 and 20 may include dispersioninterferometers such as a two wavelength source and a monitor formeasurement of an intrinsic property of a gas such as the reciprocaldispersive power in interferometry subsystem 15.

Initialization of LRI, CRI, and Interferometer System 100

In single stage lithography tools, interferometers 10, 20, 30, 40, 1010,and 1020 of interferometer system 15 do not necessarily need to beinitialized at the exchange of each wafer being processed because onlythe same stage is used for each exposure and the interferometers aremonitoring the same stage mirror at each step of the exposure and waferexchange processes. Thus, processing of information from interferometers10, 20, 30, 40, 1010, and 1020 for compensation for stationarynon-random effects of a gas and the other related effects of the gas canbe simpler in single stage lithography tools than in multi-stage tools.In contrast, in a dual stage lithography tool where stages areexchanged, interferometers 10, 20, 30, and 40 may need to be initializedat each exchange of stages if there is not a “hand off” between certaininterferometers. However, interferometers 1010 and 1020 will not need tobe initialized at each exchange of a stage or wafer chuck. The effect ofthe subsequent initializations of interferometers 10, 20, 30, and 40 onthe inversion of stationary non-random effects of a gas and otherrelated effects of the gas should be taken into account wherein theimpact of the subsequent initializations to reduce the accuracy of theinversions immediately after the initializations.

In acquisition of alignment mark measurements following immediatelyafter the initializations, one way to compensate for the reduction ofaccuracy of the corresponding inversions is to increase the timeduration of the alignment mark measurements to improve statisticalaccuracy. Another way to reduce the effect of the reduction of accuracyof the inversions immediately after the initializations is to reduce thespeed of the stage motion which reduces the amount of stationarynon-random effects of a gas and other related effects of the gasgenerated during the period between the initialization and, for example,the first exposure of the wafer.

Compensation for Effects of Vibrations

The different properties of LRI, CRI, and interferometer system 100 canbe identified by spectral analyses of respective electric interferencesignals and compensated by frequency filtering the signal data, e.g.,before use in the data processing algorithms for information about theposition of stage 16 compensated for effects of stationary non-randomeffects of a gas and the other related effects of the gas. Vibrations,for example, generally manifest at relatively high frequencies (e.g.,about 100 Hz or more), and can be isolated using a band pass filter.

Use of Interferometry Metrology Systems with Encoder Metrology Systems

In some embodiments, interferometer systems can be used in conjunctionwith encoder systems to provide accurate measurements of a stageposition in a lithography tool. For example, stationary non-randomeffects of a gas can be measured as the change between the relativeposition measurements obtained with an interferometer metrology systemand obtained with a planar encoder metrology system that occurs betweena relatively slow scan or step and stare scan mode and the scanning modeused in the processing of a wafer.

The advantage of a relative measurement procedure such as used indisclosed embodiments is the elimination or the significant reduction ofnon-linear non-cyclic effects such as geometric errors, effects ofsurface figure errors of stage mirrors, effects of beam shear ininterferometers generated by changes in orientation of measurementobjects, and stationary effects such as generated by body deformation ofa lithography tool due to stage motion excluding the effects ofdeformation of stage mirrors due to stage motion.

A further advantage of a relative measurement procedure is that effectsof deformation of stage mirrors due to stage motion are included in themeasured values of stationary non-random effects. For the disclosedembodiments, it is not necessary to identify the relative contributionsof stationary non-random effects of a gas and of stationary non-randomeffects due to deformation of stage mirrors in the measured values ofstationary non-random effects.

The planar encoder metrology system generates information about linearand angular displacements of a measurement object with a reducedsensitivity to stationary non-random effects of the gas and stationarynon-random deformation of the measurement object which however affectthe corresponding information obtained by the interferometer metrologysystem of the measurement object. Referring to FIG. 5, for example, insome embodiments, planar encoder scales 112B and 112C are attached tostage 16 and the position of the planar encoder scale is measured usingcorresponding encoder heads 113B and 113C, respectively. Planar encoderscale 112B and head 113B are configured to monitor the location of stage16 along the y-axis, parallel to interferometer axis 22, while planarencoder scale 112C and 113C are configured to monitor the location ofstage 16 along the x-axis, parallel to interferometer axis 12. Encoderheads 113B and 113C can be in communication with electronic processor17.

A planar or linear encoder herein referred to as a planar encoder may beconfigured such that the effects of gas in the respective measurementpaths do not affect the repeatability of position measurements of theplanar encoder at the nanometer and sub-nanometer level.

The processing of information in a stage metrology system including aninterferometer metrology system and encoder metrology system generatessuperheterodyne signal quadratures and respective superheterodyne phasessuch as described in U.S. Provisional Patent Application No. 60/862,949and U.S. patent application Ser. No. 11/941,012, filed Nov. 15, 2007,where the superheterodyne phases includes effects of errors of theplanar encoder system. The entire contents of applications 60/862,949and Ser. No. 11/941,012 are incorporated herein by reference. Thesensitivity of the contribution of stationary non-random effects by theencoder metrology system to the superheterodyne phases is negligible ora significantly reduced. The classification of the negligible orsignificantly reduced sensitivity of the contribution to thesuperheterodyne phases by the encoder metrology system is based on acomparison to the sensitivity of corresponding heterodyne or homodynephases of the interferometer system to stationary non-random effects.

The phases of the superheterodyne signal quadratures include primarilyonly low frequency components such as generated by stationary non-randomeffects, other related effects of a gas, atmospheric turbulence inmeasurement and reference paths of the interferometer system and errorsof the interferometer and encoder metrology systems such as cyclicerrors, non-linear non-cyclic errors, geometric errors, Abbé offseterrors, and effects of changes in temperature of the lithography tool.The phases of the superheterodyne signal quadratures can be subsequentlyprocessed to measure in situ the changes that are generated by changingfor example from a step and stare mode to a scanning mode. Thestationary non-random effects are obtained as the average of themeasured phases of the superheterodyne signal quadratures for thedifferent scan modes to reduce the contributions of random effects andstatistical errors such as arise in electronic processing.

Measurement of Stationary Effects Not Related to Gas Effects

Effects of stationary non-random effects not related to the gas, e.g.,body deformations from stage motion and changes in the temperature ofthe lithography tool, can introduce errors in, e.g., measurements madeby a CRI. Changes in the temperature of the lithography tool willgenerally contribute to errors in measurements made by a CRI atfrequencies below or of the order of 0.01 Hz. However, stationarynon-random effects that result from body deformation generated by stagemotion can lie in the frequency range of stationary non-random effectsof the gas and other related effects of the gas.

Because of the location of a CRI, the stationary non-random effects ofthe gas in the lithography tool will, in general, be reduced compared tothe magnitude of the contribution of the stationary non-random effectsof the gas to interferometer metrology systems such as interferometersystem 100 shown in FIGS. 2 a and 2 b. As a result, the contribution ofstationary non-random effects not related to the gas, e.g., bodydeformation from stage motion, to errors in measurements made by a CRIcan be measured by a procedure analogous to the procedure used tomeasure the stationary non-random effects of the gas to interferometermetrology systems such as interferometer system 100. A correspondingsuperheterodyne phase can be generated from the signals from the encodermetrology system and from the respective CRI. The stationary non-randomeffects not related to the gas can be obtained as the average of themeasured phases of the respective superheterodyne signal quadratures forthe different scan modes to reduce the contributions of random effectsand statistical errors such as arise in electronic processing.

The contribution of stationary non-random effects not related to thegas, e.g., body deformation from stage motion, to errors in measurementsmade by a CRI can be measured in certain embodiments from informationobtained during a general alignment procedure for the lithography tool.

In embodiments, the measured contribution of stationary non-randomeffects not related to the gas to information obtained with a CRI can besubtracted from the information subsequently used in the compensationfor stationary non-random effects of the gas and other related effectsof the gas.

Cyclic Errors

In addition to compensating for variations in the optical properties ofa gas, phase measurements can be compensated for still other sources oferrors. For example, cyclic errors that are present in the lineardisplacement measurements are eliminated and/or compensated by use ofone of more techniques such as described in commonly owned U.S. patentapplication Ser. No. 10/097,365 entitled “CYCLIC ERROR REDUCTION INAVERAGE INTERFEROMETRIC MEASUREMENTS” and Ser. No. 10/616,504 entitled“CYCLIC ERROR COMPENSATION IN INTERFEROMETRY SYSTEMS,” which claimspriority to U.S. Provisional Application No. 60/394,418 entitled“ELECTRONIC CYCLIC ERROR COMPENSATION FOR LOW SLEW RATES.” Each of theutility applications and the provisional patent application are all byHenry A. Hill and the contents of each thereof are incorporated hereinin their entireties by reference.

An example of another cyclic error compensation technique is describedin commonly owned U.S. patent application Ser. No. 10/287,898 entitled“INTERFEROMETRIC CYCLIC ERROR COMPENSATION” which claims priority toU.S. Provisional Application No. 60/337,478 entitled “CYCLIC ERRORCOMPENSATION AND RESOLUTION ENHANCEMENT.” The utility application andthe provisional patent application are each by Henry A. Hill and thecontents thereof are incorporated herein in their entireties byreference.

Another example of a cyclic error compensation technique is described inU.S. patent application Ser. No. 10/174,149 entitled “INTERFEROMETRYSYSTEM AND METHOD EMPLOYING AN ANGULAR DIFFERENCE IN PROPAGATION BETWEENORTHOGONALLY POLARIZED INPUT BEAM COMPONENTS” which claims priority toU.S. Provisional Patent Application 60/303,299 entitled “INTERFEROMETRYSYSTEM AND METHOD EMPLOYING AN ANGULAR DIFFERENCE IN PROPAGATION BETWEENORTHOGONALLY POLARIZED INPUT BEAM COMPONENTS.” The utility applicationand the provisional patent application are each by Henry A. Hill andPeter de Groot and the contents both thereof are incorporated herein intheir entirety by reference.

A further example of a cyclic error compensation technique is describedin commonly owned U.S. Provisional Patent Application No. 60/314,490 andcorresponding utility application Ser. No. 10/218,968 entitled “TILTEDINTERFEROMETER” by Henry A. Hill. The contents of the provisional patentapplication and the utility application are incorporated herein in theirentireties by reference.

Other techniques for cyclic error compensation include those describedin U.S. Pat. No. 6,137,574 entitled “SYSTEMS AND METHODS FORCHARACTERIZING AND CORRECTING CYCLIC ERRORS IN DISTANCE MEASURING ANDDISPERSION INTERFEROMETRY;” U.S. Pat. No. 6,252,668 B1 entitled “SYSTEMSAND METHODS FOR QUANTIFYING NON-LINEARITIES IN INTERFEROMETRY SYSTEMS;”and U.S. Pat. No. 6,246,481 entitled “Systems And Methods ForQuantifying Nonlinearities In Interferometry Systems.” All three of thecited patents are by Henry A. Hill and the contents thereof of the threecited patents are herein incorporated in their entirety by reference.

Steps in Data Processing Algorithm

While the error compensation techniques discussed above can beimplemented in a variety of different ways, FIG. 6 shows an example ofan algorithm 600 for implementing error correction for interferometricstage mirror measurements. Step one (610) in the data processingalgorithm is the measurement of stationary non-random effects in CRI notassociated with stationary non-random effects of the gas and the otherrelated effects of the gas.

Step two (620) in the data processing algorithm is the measurement ofthe effects of vibrations in LRI, CRI, and interferometer system 100.

Step three (630) in the data processing algorithm is the measurement ofinformation from LRI, CRI, and interferometer system 100 obtained duringthe processing of a series of wafers by a lithography tool.

Step four (640) in the data processing algorithm is the compensation forthe different effects of vibrations to information from LRI, CRI, andinterferometer system 100. Step four compensates for effects ofvibrations.

Step five (650) in the data processing algorithm is the subtraction ofinformation obtained by the vibration compensated LRI from theinformation obtained from vibration compensated CRI scaled according tothe respective relative measurement beam path lengths. Step fivecompensates for adiabatic effects.

Step six (660) in the data processing algorithm is the subtraction ofinformation obtained by the vibration compensated LRI from theinformation obtained from vibration compensated interferometer system100 scaled according to the respective relative measurement beam pathlengths. Step six compensates for adiabatic effects.

Step seven (670) in the data processing algorithm is the subtraction ofinformation obtained from vibration compensated CRI (from step five) andinformation about the stationary non-random effects not related to thegas (from step one) from information obtained from vibration compensatedinformation from interferometer system 100 (from step six) scaledaccording to the respective relative measurement beam path lengths. Stepseven corresponds to compensation for non-adiabatic isotropic effects ofthe gas and other related effects of the gas and compensation forstationary non-random effects not related to the gas. The subtractionstake into account the effects of the time delay for non-adiabaticisotropic effects to be transported from CRI to interferometer system100 and the frequency domain of the non-adiabatic isotropic effects ofthe gas and other related effects of the gas.

Step eight (680) in the data processing algorithm is the inversion ofthe information from interferometer system 100 obtained in step sevenfor measured values of the stationary non-random effects of the gas andthe other related effects of the gas. Step eight corresponds todetermination of non-adiabatic non-isotropic effects of the gas andother related effects of the gas in the measurement beam paths ofinterferometer system 100.

Step nine (690) in the data processing algorithm is the subtraction ofthe inverted information about stationary non-random effects of the gasand the other related effects of the gas (obtained in step eight) fromthe information obtained in interferometer system 100 about the positionincluding the angular orientation of stage 16. Step nine corresponds tocompensation for non-adiabatic non-isotropic effects of the gas andother related effects of the gas. The subtractions take into account thefrequency domain of the non-adiabatic non-isotropic effects of the gasand other related effects of the gas.

In general, any of the analysis methods described above can beimplemented in computer hardware or software, or a combination of both.For example, in some embodiments, electronic processor 17 can be part ofa module that can be installed in a computer and connected to one ormore interferometers and/or encoders and configured to perform analysisof signals from the interferometers and/or encoders. Analysis can beimplemented in computer programs using standard programming techniquesfollowing the method and figures described herein. Program code isapplied to input data to perform the functions described herein andgenerate output information. The output information is applied to one ormore output devices such as a display monitor. Each program may beimplemented in a high level procedural or object oriented programminglanguage to communicate with a computer system. However, the programscan be implemented in assembly or machine language, if desired. In anycase, the language can be a compiled or interpreted language. Moreover,the program can run on dedicated integrated circuits preprogrammed forthat purpose.

Each such computer program is preferably stored on a storage medium ordevice (e.g., ROM or magnetic diskette) readable by a general or specialpurpose programmable computer, for configuring and operating thecomputer when the storage media or device is read by the computer toperform the procedures described herein. The computer program can alsoreside in cache or main memory during program execution. The analysismethods can also be implemented as a computer-readable storage medium,configured with a computer program, where the storage medium soconfigured causes a computer to operate in a specific and predefinedmanner to perform the functions described herein.

Lithography Tool Applications

As discussed previously, lithography tools are especially useful inlithography applications used in fabricating large scale integratedcircuits such as computer chips and the like. Lithography is the keytechnology driver for the semiconductor manufacturing industry. Overlayimprovement is one of the five most difficult challenges down to andbelow 100 nm line widths (design rules), see, for example, theSemiconductor Industry Roadmap, p. 82 (1997).

Overlay depends directly on the performance, i.e., accuracy andprecision, of the distance measuring interferometers used to positionthe wafer and reticle (or mask) stages. Since a lithography tool mayproduce $50-100 M/year of product, the economic value from improvedperformance distance measuring interferometers is substantial. Each 1%increase in yield of the lithography tool results in approximately $1M/year economic benefit to the integrated circuit manufacturer andsubstantial competitive advantage to the lithography tool vendor.

The function of a lithography tool is to direct spatially patternedradiation onto a photoresist-coated wafer. The process involvesdetermining which location of the wafer is to receive the radiation(alignment) and applying the radiation to the photoresist at thatlocation (exposure).

To properly position the wafer, the wafer includes alignment marks onthe wafer that can be measured by dedicated sensors. The measuredpositions of the alignment marks define the location of the wafer withinthe tool. This information, along with a specification of the desiredpatterning of the wafer surface, guides the alignment of the waferrelative to the spatially patterned radiation. Based on suchinformation, a translatable stage supporting the photoresist-coatedwafer moves the wafer such that the radiation will expose the correctlocation of the wafer.

During exposure, a radiation source illuminates a patterned reticle,which scatters the radiation to produce the spatially patternedradiation. The reticle is also referred to as a mask, and these termsare used interchangeably below. In the case of reduction lithography, areduction lens collects the scattered radiation and forms a reducedimage of the reticle pattern. Alternatively, in the case of proximityprinting, the scattered radiation propagates a small distance (typicallyon the order of microns) before contacting the wafer to produce a 1:1image of the reticle pattern. The radiation initiates photo-chemicalprocesses in the resist that convert the radiation pattern into a latentimage within the resist.

Interferometry metrology systems, such as those discussed previously,are important components of the positioning mechanisms that control theposition of the wafer and reticle, and register the reticle image on thewafer. If such interferometry systems include the features describedabove, the accuracy of distances measured by the systems can beincreased and/or maintained over longer periods without offlinemaintenance, resulting in higher throughput due to increased yields andless tool downtime.

In general, the lithography system, also referred to as an exposuresystem, typically includes an illumination system and a waferpositioning system. The illumination system includes a radiation sourcefor providing radiation such as ultraviolet, visible, x-ray, electron,or ion radiation, and a reticle or mask for imparting the pattern to theradiation, thereby generating the spatially patterned radiation. Inaddition, for the case of reduction lithography, the illumination systemcan include a lens assembly for imaging the spatially patternedradiation onto the wafer. The imaged radiation exposes resist coatedonto the wafer. The illumination system also includes a mask stage forsupporting the mask and a positioning system for adjusting the positionof the mask stage relative to the radiation directed through the mask.The wafer positioning system includes a wafer stage for supporting thewafer and a positioning system for adjusting the position of the waferstage relative to the imaged radiation. Fabrication of integratedcircuits can include multiple exposing steps. For a general reference onlithography, see, for example, J. R. Sheats and B. W. Smith, inMicrolithography: Science and Technology (Marcel Dekker, Inc., New York,1998), the contents of which is incorporated herein by reference.

Interferometry systems described above can be used to precisely measurethe positions of each of the wafer stage and mask stage relative toother components of the exposure system, such as the lens assembly,radiation source, or support structure. In such cases, theinterferometry system can be attached to a stationary structure and themeasurement object attached to a movable element such as one of the maskand wafer stages. Alternatively, the situation can be reversed, with theinterferometry system attached to a movable object and the measurementobject attached to a stationary object.

More generally, such interferometry systems can be used to measure theposition of any one component of the exposure system relative to anyother component of the exposure system, in which the interferometrysystem is attached to, or supported by, one of the components and themeasurement object is attached, or is supported by the other of thecomponents.

An example of a lithography tool 1100 using an interferometry system1126 is shown in FIG. 5. The interferometry system is used to preciselymeasure the position of a wafer (not shown) within an exposure system.Here, stage 1122 is used to position and support the wafer relative toan exposure station. Scanner 1100 includes a frame 1102, which carriesother support structures and various components carried on thosestructures. An exposure base 1104 has mounted on top of it a lenshousing 1106 atop of which is mounted a reticle or mask stage 1116,which is used to support a reticle or mask. A positioning system forpositioning the mask relative to the exposure station is indicatedschematically by element 1117. Positioning system 1117 can include,e.g., piezoelectric transducer elements and corresponding controlelectronics. Although, it is not included in this described embodiment,one or more of the interferometry systems described above can also beused to precisely measure the position of the mask stage as well asother movable elements whose position must be accurately monitored inprocesses for fabricating lithographic structures (see supra Sheats andSmith Microlithography: Science and Technology).

Suspended below exposure base 1104 is a support base 1113 that carrieswafer stage 1122. Stage 1122 includes a plane mirror 1128 for reflectinga measurement beam 1154 directed to the stage by interferometry system1126. A positioning system for positioning stage 1122 relative tointerferometry system 1126 is indicated schematically by element 1119.Positioning system 1119 can include, e.g., piezoelectric transducerelements and corresponding control electronics. The measurement beamreflects back to the interferometry system, which is mounted on exposurebase 1104. The interferometry system can be any of the embodimentsdescribed previously.

During operation, a radiation beam 1110, e.g., an ultraviolet (UV) beamfrom a UV laser (not shown), passes through a beam shaping opticsassembly 1112 and travels downward after reflecting from mirror 1114.Thereafter, the radiation beam passes through a mask (not shown) carriedby mask stage 1116. The mask (not shown) is imaged onto a wafer (notshown) on wafer stage 1122 via a lens assembly 1108 carried in a lenshousing 1106. Base 1104 and the various components supported by it areisolated from environmental vibrations by a damping system depicted byspring 1120.

In other embodiments of the lithographic scanner, one or more of theinterferometry systems described previously can be used to measuredistance along multiple axes and angles associated for example with, butnot limited to, the wafer and reticle (or mask) stages. Also, ratherthan a UV laser beam, other beams can be used to expose the waferincluding, e.g., x-ray beams, electron beams, ion beams, and visibleoptical beams.

In some embodiments, the lithographic scanner can include what is knownin the art as a column reference. In such embodiments, theinterferometry system 1126 directs the reference beam (not shown) alongan external reference path that contacts a reference mirror (not shown)mounted on some structure that directs the radiation beam, e.g., lenshousing 1106. The reference mirror reflects the reference beam back tothe interferometry system. The interference signal produce byinterferometry system 1126 when combining measurement beam 1154reflected from stage 1122 and the reference beam reflected from areference mirror mounted on the lens housing 1106 indicates changes inthe position of the stage relative to the radiation beam. Furthermore,in other embodiments the interferometry system 1126 can be positioned tomeasure changes in the position of reticle (or mask) stage 1116 or othermovable components of the scanner system. Finally, the interferometrysystems can be used in a similar fashion with lithography systemsinvolving steppers, in addition to, or rather than, scanners. As is wellknown in the art, lithography is a critical part of manufacturingmethods for making semiconducting devices. For example, U.S. Pat. No.5,483,343 outlines steps for such manufacturing methods. These steps aredescribed below with reference to FIGS. 8 a and 8 b. FIG. 8 a is a flowchart of the sequence of manufacturing a semiconductor device such as asemiconductor chip (e.g., IC or LSI), a liquid crystal panel or a CCD.Step 1151 is a design process for designing the circuit of asemiconductor device. Step 1152 is a process for manufacturing a mask onthe basis of the circuit pattern design. Step 1153 is a process formanufacturing a wafer by using a material such as silicon.

Step 1154 is a wafer process which is called a pre-process wherein, byusing the so prepared mask and wafer, circuits are formed on the waferthrough lithography. To form circuits on the wafer that correspond withsufficient spatial resolution those patterns on the mask,interferometric positioning of the lithography tool relative the waferis necessary. The interferometry methods and systems described hereincan be especially useful to improve the effectiveness of the lithographyused in the wafer process.

Step 1155 is an assembling step, which is called a post-process whereinthe wafer processed by step 1154 is formed into semiconductor chips.This step includes assembling (dicing and bonding) and packaging (chipsealing). Step 1156 is an inspection step wherein operability check,durability check and so on of the semiconductor devices produced by step1155 are carried out. With these processes, semiconductor devices arefinished and they are shipped (step 1157).

FIG. 8 b is a flow chart showing details of the wafer process. Step 1161is an oxidation process for oxidizing the surface of a wafer. Step 1162is a CVD process for forming an insulating film on the wafer surface.Step 1163 is an electrode forming process for forming electrodes on thewafer by vapor deposition. Step 1164 is an ion implanting process forimplanting ions to the wafer. Step 1165 is a resist process for applyinga resist (photosensitive material) to the wafer. Step 1166 is anexposure process for printing, by exposure (i.e., lithography), thecircuit pattern of the mask on the wafer through the exposure apparatusdescribed above. Once again, as described above, the use of theinterferometry systems and methods described herein improve the accuracyand resolution of such lithography steps.

Step 1167 is a developing process for developing the exposed wafer. Step1168 is an etching process for removing portions other than thedeveloped resist image. Step 1169 is a resist separation process forseparating the resist material remaining on the wafer after beingsubjected to the etching process. By repeating these processes, circuitpatterns are formed and superimposed on the wafer.

The interferometry systems described above can also be used in otherapplications in which the relative position of an object needs to bemeasured precisely. For example, in applications in which a write beamsuch as a laser, x-ray, ion, or electron beam, marks a pattern onto asubstrate as either the substrate or beam moves, the interferometrysystems can be used to measure the relative movement between thesubstrate and write beam.

As an example, a schematic of a beam writing system 1200 is shown inFIG. 9. A source 1210 generates a write beam 1212, and a beam focusingassembly 1214 directs the radiation beam to a substrate 1216 supportedby a movable stage 1218. To determine the relative position of thestage, an interferometry system 1220 directs a reference beam 1222 to amirror 1224 mounted on beam focusing assembly 1214 and a measurementbeam 1226 to a mirror 1228 mounted on stage 1218. Since the referencebeam contacts a mirror mounted on the beam focusing assembly, the beamwriting system is an example of a system that uses a column reference.Interferometry system 1220 can be any of the interferometry systemsdescribed previously. Changes in the position measured by theinterferometry system correspond to changes in the relative position ofwrite beam 1212 on substrate 1216. Interferometry system 1220 sends ameasurement signal 1232 to controller 1230 that is indicative of therelative position of write beam 1212 on substrate 1216. Controller 1230sends an output signal 1234 to a base 1236 that supports and positionsstage 1218. In addition, controller 1230 sends a signal 1238 to source1210 to vary the intensity of, or block, write beam 1212 so that thewrite beam contacts the substrate with an intensity sufficient to causephotophysical or photochemical change only at selected positions of thesubstrate.

Furthermore, in some embodiments, controller 1230 can cause beamfocusing assembly 1214 to scan the write beam over a region of thesubstrate, e.g., using signal 1244. As a result, controller 1230 directsthe other components of the system to pattern the substrate. Thepatterning is typically based on an electronic design pattern stored inthe controller. In some applications the write beam patterns a resistcoated on the substrate and in other applications the write beamdirectly patterns, e.g., etches, the substrate.

An important application of such a system is the fabrication of masksand reticles used in the lithography methods described previously. Forexample, to fabricate a lithography mask an electron beam can be used topattern a chromium-coated glass substrate. In such cases where the writebeam is an electron beam, the beam writing system encloses the electronbeam path in a vacuum. Also, in cases where the write beam is, e.g., anelectron or ion beam, the beam focusing assembly includes electric fieldgenerators such as quadrapole lenses for focusing and directing thecharged particles onto the substrate under vacuum. In other cases wherethe write beam is a radiation beam, e.g., x-ray, UV, or visibleradiation, the beam focusing assembly includes corresponding optics andfor focusing and directing the radiation to the substrate.

Other embodiments are in the following claims.

1. A system, comprising: a moveable stage configured to support a waferand position the wafer relative to a projection lens; a firstinterferometer configured to direct a first measurement beam along apath between a first measurement object attached to the projection lensand a first interferometer assembly located remote from the projectionlens, the first interferometer being configured to form a first outputbeam from the first measurement beam, the first output beam comprising afirst interferometric phase comprising information about variations inan optical path length of the path between the first measurement objectand the first interferometry assembly; a first detector configured todetect the first output beam; a second interferometer configured todirect a second measurement beam along a path between a secondmeasurement object attached to the stage and a second interferometerassembly located remote from the stage, the second interferometer beingconfigured to form a second output beam from the second measurementbeam, the second output beam comprising a second interferometric phasecomprising information about variations in an optical path length of thepath between the second measurement object and the second interferometryassembly; a second detector configured to detect the second output beam;an electronic processing system in communication with the first andsecond detectors, the electronic processing system being programmed tomonitor a degree of freedom of the stage based on the secondinterferometric phase and to reduce uncertainty in the monitored degreeof freedom due to variations in the optical properties in a gas in thepath of the second measurement beam based on the first and secondinterferometric phases.
 2. The system of claim 1, wherein the first andsecond measurement beam paths are in a path of a gas flow of gasintroduced into an enclosure housing the stage.
 3. The system of claim2, wherein the first and second measurement beam paths are parallel. 4.The system of claim 2, wherein the first measurement beam path issufficiently far from the stage so that gas turbulence due to movementof the stage does not cause substantial variations in the opticalproperties of the gas in the first measurement path.
 5. The system ofclaim 1, wherein the first interferometer is a column referenceinterferometer.
 6. The system of claim 1, wherein the secondinterferometer is a multi-axis interferometer.
 7. The system of claim 6,wherein the second interferometer comprises a single passinterferometer.
 8. The system of claim 6, wherein the secondinterferometer comprises a plurality of single pass interferometers. 9.The system of claim 6, wherein the second interferometer comprises abeam conditioning assembly.
 10. The system of claim 1, wherein themeasurement object is a plane minor measurement object.
 11. The systemof claim 1, further comprising a third interferometer positioned remotefrom the stage, the third interferometer being a fixed measurement beampath interferometer where the measurement beam path is isolated from thegas in the second measurement beam path.
 12. The system of claim 11,wherein the third interferometer is positioned close to the secondinterferometer.
 13. The system of claim 11, further comprising a thirddetector configured to detect a third output beam from the thirdinterferometer, the third detector being in communication with theelectronic processing subsystem and the electronic processing subsystembeing configured to reduce uncertainty in the monitored degree offreedom due to variations in the optical properties of the gas based onthe information in the third output beam.
 14. The system of claim 11,further comprising a plurality of interferometers including the thirdinterferometer, the plurality of interferometers being positioned atlocations remote from the stage, each of the plurality interferometersbeing fixed measurement beam path interferometers where the measurementbeam path of each is isolated from the gas in the second measurementbeam path.
 15. The system of claim 11, wherein the third interferometeris a wavelength meter.
 16. The system of claim 1, further comprising anoptical encoder configured to monitor a degree of freedom of the stage.17. A lithography system for use in fabricating integrated circuits on awafer, the system comprising: a projection lens for imaging spatiallypatterned radiation onto the wafer; the system of claim 1 for monitoringthe position of the wafer relative to the imaged radiation; and apositioning system for adjusting the position of the stage relative tothe imaged radiation, wherein the wafer is supported by the stage. 18.The lithography system of claim 17, wherein the lithography system is adual stage lithography system.
 19. A lithography system for use infabricating integrated circuits on a wafer, the system comprising: anillumination system including a radiation source, a mask, a positioningsystem, a projection lens, and the system of claim 1, wherein duringoperation the source directs radiation through the mask to producespatially patterned radiation, the positioning system adjusts theposition of the mask relative to the radiation from the source, theprojection lens images the spatially patterned radiation onto the wafersupported by the stage, and the system monitors the position of the maskrelative to the radiation from the source.
 20. The lithography system ofclaim 19, wherein the lithography system is a dual stage lithographysystem.
 21. The lithography system of claim 19, wherein the lithographysystem is an immersion lithography system.